| Mo, 15.6. 17:00 - 19:00 | Possibility for Pre-Registration @ Assemby Hall | 17:00 - 19:00 | ||||||
| Tu, 16.6. 08:00 - 09:00 | Registration opens | 08:00 - 09:00 | ||||||
| Tu, 16.6. 09:00 - 09:15 | IFASD 2026 Opening Remarks | 09:00 - 09:15 | ||||||
| Tu, 16.6. 09:15 - 09:30 | Welcome Address DGLR/CEAS | 09:15 - 09:30 | ||||||
| Tu, 16.6. 09:30 - 09:45 | Welcome Adress by GERMAN AEROSPACE CENTER | 09:30 - 09:45 | ||||||
| 0.1 Tu, 16.6. 09:45 - 10:30 | Plenary 1 Chair: L. Tichy, German Aerospace Center, DE | |||
| 09:45 | 10:30 |
Reduced Complexity: The Essence of a Complex Journey Involving Language, Mathematics, and Emotions Walt Silva, Emeritus Langley Associate | ||
| Coffee Break | 10:30 - 11:00 | |||||||
| 1.11 Tu, 16.6. 11:00 - 13:00 | Aeroelasticity in Conceptual Aircraft Design 1 Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 11:00 | 11:30 | 0205 |
Aircraft-Level Aeroelastic Optimization Using Global-Local Structural Modeling S.-K. Kilimtzidis, University of Patras, GR This work presents an aircraft-level aeroelastic structural optimization framework for early design. A global–local modeling strategy is adopted, where local composite strength behavior is represented using CUF-based high-order theories, while global aeroelastic response is captured using panel aerodynamics, enabling multi-scale aeroelastic design consistency. | |
| 11:30 | 12:00 | 0312 |
Influence of material properties on the aeroelastic response of a T-tail laminated composite structure G. Comand, Sorbonne Université, FR The aim of this study is to perform the optimisation of the aeroelastic response of a T-tail composite structure, based on a two-level approach for the representation of the behaviour of composite laminates via the polar representation of anisotropic elasticity. This approach allows to globally explore the whole feasible domain of composite laminates, as well as to study the influence of parametric uncertainties (i.e. errors on ply angles and thicknesses) on the aeroelastic response. | |
| 12:00 | 12:30 | 0032 |
An Efficient Geometrically Nonlinear Aeroelastic Framework for Gradient-Based Aeroelastic Optimization C. A. Lupp, Air Force Research Laboratory, US Past work has applied geometrically nonlinear beam formulations to MDO, using gradient approximations or automatic differentiation. This work improves Su and Cesnik's strain-based beam formulation and extends it to obtain analytical and exact derivatives. The paper will demonstrate that these derivatives enable fast and efficient optimization during conceptual design. | |
| 12:30 | 13:00 | 0245 |
Local Optimization Model Refinement for the Preliminary Aeroelastic Structural Design of a Transport Aircraft Wing M. Schulze, German Aerospace Center (DLR), DE Local effects like loads at the landing gear attachment can affect a large area of the structural optimization and thus lead to an increased stiffness and mass of the load-bearing wing. A local refinement at significant regions of the optimization model can be an adequate solution to improve the structural design while keeping the simulation time within reasonable limits for an early design stage. |
| 1.12 Tu, 16.6. 11:00 - 13:00 | Computational Aeroelasticity 1 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 11:00 | 11:30 | 0083 |
NONLINEAR ANALYSIS OF A DAMPED PITCH-HEAVE AEROELASTIC SYSTEM WITH STRUCTURAL NONLINEARITY B. M. Castro, Embraer, BR This work establishes a framework for developing and designing the damping characteristics of a nonlinear system for a specific purpose. In this case, the design targets the occurrence of LCO, in a predefined range of wind tunnel conditions, and an intended nonlinear behavior (LCOs and bifurcation points) within the operational parameter space of the experimental infrastructure. Novelty lies in the experiment itself and in the use of a new mathematical model of nonlinearity that will be used in the experiments. The developed framework can be used to study nonlinear phenomena associated with damping that may occur in real aircraft. | |
| 11:30 | 12:00 | 0084 |
NONLINEAR AEROELASTIC SIMULATIONS OF A QUADRATIC DAMPER WITH FREEPLAY IN A 3-DOF TYPICAL SECTION B. M. Castro, Embraer, BR This work aims to simulate a three-degree-of-freedom typical section both in frequency and time domains. A nonlinearity of a quadratic damper with freeplay is assumed to exist in the degree of freedom associated with the control-surface rotation. The present model can capture the behavior of a nonlinear damper with quadratic damping and freeplay in both frequency and time domains and it appears to capture characteristics (amplitude and frequency) of eventual LCO in a more accurate fashion. | |
| 12:00 | 12:30 | 0167 |
Limit Cycle Oscillation predictions using the Harmonic Balance Method and the nonlinear Source and Doublet Panel Method V. Laraspata, Politecnico di Bari, IT Nonlinear aeroelastic systems can undergo self-excited periodic responses, known as Limit Cycle Oscillations, which can be predicted numerically using time integration or more efficient frequency domain techniques, such as the Harmonic Balance Method. In this work, we demonstrate the intricacies of using the HBM in nonlinear aeroelastic analysis of systems with frequency-domain aerodynamic loads. | |
| 12:30 | 13:00 | 0207 |
Prediction of freeplay-induced aeroelastic limit cycle oscillations using the Loewner framework D. Quero, DLR, DE An efficient approach is presented to incorporate frequency-domain unsteady aerodynamics into nonlinear aeroelastic simulations driven by structural freeplay. Loewner-based state-space realizations are constructed from frequency-response data, enabling efficient limit-cycle prediction with transonic aerodynamics using either time-domain simulation or harmonic balance in the frequency domain. |
| 1.13 Tu, 16.6. 11:00 - 13:00 | Wind Tunnel and Flight Testing 1 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 11:00 | 11:30 | 0184 |
EXPERIMENTAL ASSESSMENT OF GUST LOAD ALLEVIATION TECHNOLOGIES FOR HIGH ASPECT RATIO ULTRA EFFICIENT REGIONAL A/C. WING G.M. Carossa, Politecnico di Milano, IT HERWINGT delivers an iso?frequency?scaled AR16 wing demonstrator enabling high?fidelity validation of active GLA. The campaign confirms ASE modelling, scaling and control?law integration methods, demonstrating significant load reduction and providing robust experimental evidence to advance lightweight high?AR wing technologies toward full?scale application | |
| 11:30 | 12:00 | 0152 |
EXPERIMENTAL WIND TUNNEL TESTING OF A REINFORCEMENT LEARNING BASED GUST LOAD ALLEVIATION SYSTEM ON A FLEXIBLE WING R Konatala, DLR, DE This research demonstrates the sim-to-real transfer of a Soft Actor-Critic reinforcement learning controller for active gust load alleviation on a flexible wing. Novelty lies in a data-driven framework trained using data generated from a linear aeroelastic model, which successfully generalizes to physical hardware, validated through wind tunnel experiments. | |
| 12:00 | 12:30 | 0204 |
DIRECTLY-PHYSICAL SUBSPACE IDENTIFICATION FOR STRUCTURE-PRESERVING AEROSERVOELASTIC MODEL UPDATING Ö. Süelözgen, DLR, German Aerospace Center, DE Accurate aeroservoelastic (ASE) models are essential for flutter prediction, stability assessment, and control-law development, yet in practice they often require extensive manual tuning due to structural uncertainty, unsteady aerodynamic modeling errors, and actuator/sensor dynamics not fully captured by nominal analysis models. Due to the inherent assumptions of the theory, the ASE models comprised of previously mentioned subsystems always contain a degree of modeling error and uncertainty, i. e. in practice, these models are useful for predicting the aircraft aeroelastic response, but they are not perfect. Thus, ASE models have to be updated on the basis of available input-output data from ground and flight tests until there is a satisfactory correlation between model predictions and experimental results. In practice, model updating remains labor-intensive because standard identification methods either (i) fit low-order black-box models that do not map cleanly back to physical parameters, or (ii) perform output-error tuning on high-order models with weak identifiability and limited robustness to sensor and actuator dynamics. This paper addresses the research question: How can a low-order, data-driven subspace model identified from wind-tunnel tests be used to update a high-order, physically structured ASE model while enforcing physical consistency and stability? We propose Directly-Physical Subspace Identification (DPSI), a structure-preserving model updating methodology that uses subspace identification only to extract a black-box state-space model from measured data, and then estimates a compact set of physical parameters by constrained nonlinear optimization. | |
| 12:30 | 13:00 | 0188 |
Transonic wind tunnel testing of Switchable Vortex Generators for Load Alleviation and Stall Control L. Marino, TU Delft, NL This work presents the design and wind-tunnel investigation of novel switchable vortex generator concepts based on a rotating vane. Active and semi-active implementations are developed to enable multiple flow-control functions within a single device, and their mechanical design and transonic experimental assessment are described. |
| 1.14 Tu, 16.6. 11:00 - 13:00 | Aeroservoelasticity 1 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 11:00 | 11:30 | 0085 |
Validation of a LFD Based Workflow for Active Damping Augmentation using Experimental Data Boris Micheli, DLR, DE The work validates a LFD-based workflow for aeroservoelastic activities using experimental data. The workflow provides accurate state space models for control activities and permits CSM-CFD simulations incorporating controller dynamics to capture phenomena that lie beyond DLM capabilities. The validation of the workflow was also a necessary step to enable its application to transonic experiments. | |
| 11:30 | 12:00 | 0082 |
Sensitivity Analysis of Structural-Aerodynamic Sensor Fusion Configuration for Active Flutter Suppression K Lay, Georgia Institute of Technology, US This work focuses on the active flutter suppression based on structural-aerodynamic sensor fusion, demonstrating that it outperforms inertial sensors alone. Time-domain aeroservoelastic numerical model will be used to analyzed various configurations of inertial and pressure sensor configurations that optimized the closed-loop flutter speed, providing guidelines for robust and reliable AFS systems. | |
| 12:00 | 12:30 | 0065 |
Actuator-friendly flutter control design utilizing robust control and blending of inputs and outputs Till Strothteicher, DLR Institute of Flight Systems, DE A novel active flutter suppression method for civil aircraft is presented. The structured control synthesis allows for implementation of robustness constraints in the controller design and minimizes control effort, overcoming limitations of previous methods. An arbitrary number of aeroelastic modes can be decoupled and damping augmented, which has great value for industrial-scale applications. | |
| 12:30 | 13:00 | 0285 |
LPV-Based Co-Design of Baseline Flight Control and Active Flutter Suppression with Control Surface Size Optimization Zs-W Wermeser, HUN-REN Institute for Computer Science and Control, HU This paper presents an LPV-based co-design framework integrating controller synthesis and control surface optimization for baseline flight control and active flutter suppression of flexible aircraft. Applied to the mini MUTT UAV, the approach enables early-stage, control-oriented assessment of stability and performance while explicitly accounting for airspeed- and structure-dependent coupling. |
| 1.15 Tu, 16.6. 11:00 - 13:00 | Experimental Methods in Structural Dynamics and Aeroelasticity 1 Chair: N.N. | ALTE MENSA - Room Taberna |
| 11:00 | 11:30 | 0212 |
Uncertainty quantification in automated modal shape sensing of a high-aspect-ratio wing J. Gundlach, German Aerospace Center (DLR), DE This work demonstrates online modal shape sensing with experimentally identified modes and identification-related uncertainty on a high-aspect-ratio wing. By continuously updating identified modes, the approach provides displacement estimates with confidence bounds under realistic conditions. This enables reliable monitoring of deformation-induced modal changes in wind tunnel and flight testing. | |
| 11:30 | 12:00 | 0223 |
Experimental Identification of Modal Parameters in a Semi Aeroelastic Hinged Wing Demonstrator J. M. Ledo da Cunha, German Aerospace Center, DE Experimental identification of modal parameters is conducted for a laboratory wing equipped with a semi?aeroelastic hinge demonstrator. The study characterizes the system’s dynamic behaviour under variable hinge angle and stiffness settings. The resulting dataset and identified models provide a basis for development of flight test data correction procedures. | |
| 12:00 | 12:30 | 0117 |
EXPERIMENTAL INVESTIGATION OF A WHIRL FLUTTER USING NOVEL 2 DOF SMALL-SCALE ROTOR-PYLON RIG A.P. Petkov, University of Bristol, GB A novel small-scale 2-DOF pendulum-mounted rotor–pylon rig, based on an adapted Reed model including gravitational stiffness, is used to map whirl-flutter stability boundaries. The resulting data support numerical validation and parametric studies provide fruitful insights into future tiltrotor design choices. | |
| 12:30 | 13:00 | 0280 |
EXPERIMENTAL INVESTIGATION ON THE EFFECT OF PROPELLER PLACEMENT ON THE AEROELASTIC BEHAVIOUR OF FLEXIBLE WINGS A-P Pontillo, UWE Bristol, GB This work aims to predict and analyse the behaviour of flexible wings subjected to vibrations induced by a propeller. In addition to addressing common issues like whirl flutter, it seeks to parameterise the position and offset of the propeller axis relative to the wing's elastic axis and to map the wing's aeroelastic response to the propeller's influence. |
| Networking Lunch & Poster Session | 13:00 - 14:15 | |||||||
| 2.11 Tu, 16.6. 14:15 - 16:15 | Aeroelasticity in Conceptual Aircraft Design 2 Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 14:15 | 14:45 | 0214 |
Effects Of Elasticity On Aeroelastic-Flight-Dynamic Characteristics Of Flying Wing Aircraft J. Zhou, Northwestern Polytechnical University, CN This work establishes a rigid-elastic coupled flight dynamics model for high-aspect-ratio flying wings based on the mean-axis method. It reveals structural elasticity boosts short-period mode damping, reduces CAP, and impacts stability/control. Valuable for scientific research and aircraft design, offering theoretical/engineering guidance. | |
| 14:45 | 15:15 | 0037 |
SHAPE AND SIZING AEROELASTIC GUST OPTIMIZATION OF A X-56 PLANFORM WITH STRESS CONSTRAINTS J.D. Deslich, U.S. Air Force Research Laboratory, US This work will explore gradient-based optimization with shape and sizing design variables for aeroelastic gust loads. The presented methods offers efficient gradient calculations of stress sensitivities and enables the inclusion of aeroelastic gust design earlier in the aircraft design process. | |
| 15:15 | 15:45 | 0111 |
Investigation of Non-linear Structural Dynamics and Aeroelastic Properties of Strut-Braced Wings in a Conceptual Design D. J. Colombo-Acquarone, DLR, DE The paper presents design investigations of a strut-braced wing aircraft. Parametric studies of strut attachment position on the wing, strut sweep angle, and lift distribution are performed. The influence of an L-shape junction between wing and strut on structural sizing is investigated. A comparison of linear and non-linear methods is performed, regarding loads, deformation and eigenmodes. | |
| 15:45 | 16:15 | 0153 |
Nonlinear aeroelasticity of Strut-Braced High Aspect Ratio Wings M.A. Amoozgar, University of Nottingham, GB Strut-braced high aspect ratio wings are proposed to overcome the aeroelastic limitations of high aspect ratio wings, but their nonlinear aeroelasticity has not been fully understood. This paper investigates the nonlinear aeroelasticity of SB-HARW (using a nonlinear beam formulation and an unsteady aerodynamics), emphasizing the role of strut parameters on pre and post-instability of the wing. |
| 2.12 Tu, 16.6. 14:15 - 16:15 | Computational Aeroelasticity 2 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 14:15 | 14:45 | 0020 |
Transonic Aeroelastic Analysis of the X-59 Aircraft Using FUN3D W. A. Silva, NASA, US The Low-Boom Flight Demonstrator (LBFD), or X-59 aircraft, was designed and fabri- cated by the Lockheed-Martin (LM) Corporation under a contract from NASA as part of the QueSST Mission. One of the primary goals is to demonstrate that a low sonic boom is achievable via aerodynamic shaping. The aircraft successfully completed its first flight, marking the beginning of an extensive envelope expansion campaign. In continued prepa- ration for first flight and flight envelope expansion, the combined NASA/LM X-59 team prepared several documents towards Airworthiness Certification including various tests and analyses. Given that the aircraft will reach a maximum Mach number of 1.4, a transonic aeroelastic analysis has been generated to address any potential concerns. Three different methods, all based on the FUN3D code, were used to generate these solutions: FUN3D, FUN3D/AEROM, FUN3D/Linearized Frequency Domain (LFD). Results are presented for four Mach numbers: M=0.95, 0.97, 0,99, and 1.05. | |
| 14:45 | 15:15 | 0216 |
Nonlinear aeroelastic simulations of low-boom supersonic transport aircraft K Soneda, Japan Aerospace Exploration Agency, JP The low-drag and low-boom performance requirements for supersonic transport impose strict and unique requirements on the airframe design. The fuselage bending can be coupled with the wing bending/torsion. The nonlinear aeroelasticity of low-boom supersonic transport aircraft design by JAXA will be numerically investigated using the finite element model and computational fluid dynamics. | |
| 15:15 | 15:45 | 0060 |
Flutter analysis of missile configurations at transonic speeds by the not-so-slender wing/body theory M Chimeno, Universidad Politécnica de Madrid, ES The proposed work can be a very valuable design tool for industry for the computation of aeroelastic stability and flutter of missile configurations in the transonic Mach number range. Upgrading existing methodologies to include elastic deformations and avoiding the limitation of low frequency oscillations the method can be a good complement to more sophisticated ones like CFD. | |
| 15:45 | 16:15 | 0019 |
Fully Coupled CFD-FEM Analysis of the HyMAX Geometry Modified to Induce Flutter T.Y. Xu, Duke University, US This study couples FUN3D with a FEM code to identify the flutter point on a modification of the HyMAX experiment. This work provides insights into potential modifications of an existing hypersonic experiment from the AIAA Aeroelastic Prediction Workshops to induce stronger fluid-structure coupling and expands the database of computational results of thin plates subjected to non-symmetric flows. |
| 2.13 Tu, 16.6. 14:15 - 16:15 | Wind Tunnel and Flight Testing 2 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 14:15 | 14:45 | 0233 |
UNSTEADY PRESSURE AND DEFORMATION MEASUREMENTS USING PSP AT THE ONSET OF LIMIT CYCLE FLUTTER K. Saitoh, JAXA, JP Wind tunnel testing was performed to measure unsteady pressure and structural deformation of an aeroelastic wing model at transonic flutter using lifetime?based PSP and high?speed stereo cameras. Despite challenges in PSP application and optical interference, the test successfully captured pressure fields and flutter motion, enabling detailed analysis of the aeroelastic behavior. | |
| 14:45 | 15:15 | 0291 |
âSHIFT THE DIPâ â AEROELASTIC EFFECTS OF SHOCK-CONTROL BUMPS ON A SUPERCRITICAL AIRFOIL IN TRANSONIC FLOW A. Altkuckatz, DLR, DE This study provides a quantitative experimental assessment of shock-control-bump induced flow-structure interaction in the transonic dip using pressure sensors, accelerometers and time-resolved iPSP. Results show a strong stabilization of the flutter boundary and reveal a regime change from heave to torsion dominated flutter at higher Mach numbers. | |
| 15:15 | 15:45 | 0265 |
Design of a Swept Wing Model for the Investigation of Semi-Active Flutter Suppression in Transonic Flow J. Nitzsche, Institute of Aeroelasticity, German Aerospace Center (DLR), DE A swept cantilever wing is numerically designed for a dedicated transonic flutter experiment in the DNW-TWG. CFD-based frequency- and time-domain flutter analyses predict a pronounced transonic dip for the clean configuration. Localized contour bumps are shown to significantly increase the flutter boundary near the dip, providing the basis for forthcoming experimental validation. | |
| 15:45 | 16:15 | 0281 |
Aerodynamic and Aeroelastic Characterization of a Forward-Swept, Laminar Aircraft Wing under Realistic Flight Conditions T. G. Schmidt, Deutsches Zentrum für Luft- und Raumfahrt DLR e.V., DE To reduce emissions, novel wing designs are sought after. Among other strategies, a promising approach are forward-swept wing, naturally laminar wing configurations, which may offer aerodynamic benefits. Yet they come with aeroelastic challenges. To address those, wind tunnel results conducted for a wing model at realistic (full-scale Mach and Reynolds numbers) flight conditions are characterized. |
| 2.14 Tu, 16.6. 14:15 - 16:15 | Aeroservoelasticity 2 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 14:15 | 14:45 | 0086 |
Gust Load Alleviation for Highly Flexible Aircraft in an Integrated Aeroelastic and Flight Dynamic Framework MN Naseer, NUST, PK An integrated aeroelastic, flight dynamics and control design mathematical model is developed in SIMULINK to account for flexibility effects in flight dynamic behavior during gust encounters and alleviate the wing loadings for the High-Altitude Long Endurance Unmanned Ariel Vehicles. These HALE UAVs are made of light-weight materials like fiber composites and have high aspect ratio wings to cater for high endurance requirements. Hence these structures are highly flexible which requires a robust control system that should make the system stable and controllable. Moreover, the structural flexibility brings the low frequency structural modes close to the rigid body modes which necessitates an approach that unifies both these rigid and flexible motions. Along with this, highly flexible structures require a robust control system that should make the system stable and controllable. This brings all the major subjects related to aircraft design namely structural dynamics, aerodynamics, flight dynamics and controls under one umbrella known as AeroServoElasticity. In order to cater for these requirements , a generic high aspect ratio flexible glider from MSC Nastran example is used to numerically demonstrate a framework which measures flutter margins and limit cycle oscillation behavior for various flight maneuvers and gust encounters and alleviates the wing loadings when required. Structural equations of motion are modelled in SIMULINK based on mass and stiffness matrices obtained from SOL103 of MSC NASTRAN. A structural dynamics block is thus developed which results in time based nodal displacements and its derivatives. Vortex Lattice Method is used to develop aerodynamic model in DynaFlight Software. This aerodynamic model results in Aerodynamic Influence Coefficients and spline matrices. These aerodynamic matrices are imported in SIMULINK and coupled with structural dynamic block. Aeroelastic responses are measured against given flight conditions. Nonlinear equations of | |
| 14:45 | 15:15 | 0028 |
Maneuver Load Alleviation Function Design Employing a Load Estimator M. Lopes Silva, Airbus Operations SAS, FR This work introduces a new approach for designing maneuver load alleviation functions. The proposed methodology employs a robust load estimator designed in previous research and does not rely on real-time optimization. Validation across the entire flight envelope, including various conditions and mass configurations, confirms that aircraft loads are effectively reduced to the proposed envelope. | |
| 15:15 | 15:45 | 0208 |
Model Predictive Control with Adaptive Prediction Horizon for Load Alleviation in Very Flexible Aircraft C. Cesnik, The University of Michigan - Ann Arbor, US This work proposes an adaptive prediction horizon strategy for model predictive control applied to load alleviation in very flexible aircraft. By dynamically reducing the horizon during constraint-active phases with terminal penalty correction, the method preserves recursive feasibility and stability while significantly lowering computational cost, enabling more tractable real-time aeroservoelastic control. | |
| 15:45 | 16:15 | 0284 |
ACTIVE GUST LOAD ALLEVIATION ON A FULL-SCALE AIRCRAFT WING USING AN ADAPTIVE FOLDING WINGTIP MECHANISM M. Ahmadi, adana science and technology university, TR Integrated aeroservoelastic modeling and nonlinear MPC are developed to use an adaptive folding wingtip for active gust load alleviation on a flexible high aspect ratio transport wing. A reduced order unsteady aeroelastic plant with gust and actuator dynamics enables constrained multi objective control and hybrid sensing. Simulations show 20 to 40% peak wing root bending moment reduction. |
| 2.15 Tu, 16.6. 14:15 - 16:15 | Experimental Methods in Structural Dynamics and Aeroelasticity 2 Chair: N.N. | ALTE MENSA - Room Taberna |
| 14:15 | 14:45 | 0162 |
CFD-Based Reconstruction of In-Flight Aerodynamic Loads on a Dassault Falcon 8X M. Cheikh, Dassault Aviation, FR A test campaign of three flights was conducted on the Falcon 8X development aircraft in 2024. Instrumentation consisted of parietal pressure pads and a digital image correlation system enabling wing shape measurements. This paper presents the test campaign and its analysis relying upon a CFD-based reconstruction of loads and comparisons with pressure measurements in various flight conditions. | |
| 14:45 | 15:15 | 0269 |
Experimental benchmark wing-box with adjustable stiffness and controlled nonlinearities for structural dynamics I. Gal, University of Liverpool, GB An experimental wing-box benchmark is developed with the capability to deliberately introduce stiffness uncertainties and nonlinear effects present in real flight wing deflection. This enables systematic use of ground testing data to understand discrepancies with models and to improve structural predictions for existing and future flexible wings. | |
| 15:15 | 15:45 | 0088 |
DEVELOPMENT OF AEROELASTIC PITCH-HEAVE WING TEST RIG WITH NONLINEAR DAMPER-FREEPLAY MECHANISM X Chi, University of Bristol, GB This work presents a novel 2-DoF heave-pitch rig with an adjustable damper-freeplay mechanism to introduce and characterise structural nonlinearities. It enables a systematic study of LCO onset and bifurcations under varying damping and freeplay. The high-fidelity data also provides a critical benchmark for validating reduced-order nonlinear models, advancing predictive aeroelastic capabilities. | |
| 15:45 | 16:15 | 0109 |
Physics-Informed Ground Vehicle Test Mode Expansion for Flutter Analysis E. C. Chung, Seoul University, KR To overcome the limitations of geometry-only interpolation like SPLINE, this paper proposes an AGMD-Kriging framework that expands sparse GVT data into full-field modes. It accurately captures physics-informed characteristics of complex structures without computationally expensive FEM tuning, significantly enhancing the reliability of aeroelastic predictions. |
| Coffee Break | 16:15 - 16:45 | |||||||
| 3.11 Tu, 16.6. 16:45 - 18:45 | Aeroelasticity in Conceptual Aircraft Design 3: Flutter/LCO Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 16:45 | 17:15 | 0106 |
FLUTTER SOLUTION METHODS UNDER UNCERTAINTIES OF THE JOBY EVTOL AIRCRAFT M Castellani, Joby Aviation, US This paper presents a comparison of the continuation method and structured singular value (mu) analysis for assessing the impact of uncertainties on aircraft flutter. The two methods are applied for a real industrial test case, the Joby S4 eVTOL aircraft, and specifically focusing on whirl flutter. The continuation method allows an efficient solution of the flutter problem and tracking of modal frequencies and damping vs. speed. The speed can be replaced by any other continuation parameter, namely an uncertain parameter. The mu analysis framework is a widely used robust stability tool used in the control systems field, but it can be extended to deal with flutter problems too. | |
| 17:15 | 17:45 | 0148 |
SDPMflut: an open-source unsteady Source and Doublet Panel method for flutter analysis G. Dimitriadis, University of Liege, BE SDPMflut is an open-source Python code for unsteady aerodynamic and flutter analysis of complete subsonic aircraft configurations, using the unsteady compressible Source and Doublet Panel Method. The paper describes the theoretical basis of the method and presents several validation test cases. | |
| 17:45 | 18:15 | 0137 |
Prediction of Limit Cycle Oscillations on the Pazy Wing with mid-fidelity aerodynamic methods A Bove, Politecnico di Milano, IT The work investigates the Pazy Wing to determine the nature of its limit cycles, by coupling a nonlinear structural beam model with diverse aerodynamic methods. The results show that the observed LCOs originate from nonlinear structural effects, providing guidance for the selection of efficient modelling approaches and highlighting the need for 3D aerodynamics to correctly assess the LCO severity | |
| 18:15 | 18:45 | 0159 |
Coupled nonlinear aeroelastic stability of wing-propeller systems M.A. Amoozgar, University of Nottingham, GB In this paper, a fundamental aeroelastic model is developed to predict the instability boundaries of a wing-rotor system. Two types of nonlinearities are available which are the wing hardening and the pylon freeply nonlinearities. The developed aeroelastic model is used to investigate the transition from wing flutter to whirl flutter as well as the post-flutter behaviour of this coupled system. |
| 3.12 Tu, 16.6. 16:45 - 18:45 | Computational Aeroelasticity 3 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 16:45 | 17:15 | 0277 |
Aeroelastic Optimization for Dynamic Model Adjustment Based on Ground- / Flight Test Data and Increased Stability Margin W. R. Krüger, DLR German Aerospace Center, DE The paper presents the process and an example for adjustment of the dynamic model of a transport aircraft, using optimization in NASTRAN, based on ground- and flight test data. Furthermore, an example for an aeroelastic optimization process of a transport aircraft wing, aiming at an increased aeroelastic stability margin, also using NASTRAN, is described in the paper. | |
| 17:15 | 17:45 | 0027 |
Efficient Computation of Design Derivatives for Aeroelastic Systems B. Preston, Imperial College London, GB Methods for obtaining design derivatives of time-domain aeroelastic analysis and flutter for flexible aircraft configurations are presented that leverage the Google JAX machine learning framework. This allows for efficient gradient-based design optimization for a coupled UVLM aerodynamic and beam structure formulation with respect to multiple aerodynamic and structural design parameters. | |
| 17:45 | 18:15 | 0199 |
SHAPE SENSITIVITY OF WING BOX PANELS IN AN AUTOMATED STRUCTURAL OPTIMIZATION SYSTEM (ASTROS) A. Coffing, Virginia Polytechnic Institute and State University, US A novel enhancement to the Continuum Sensitivity Analysis (CSA) method is presented in the Nastran-compatible ASTROS software. This method allows the boundary velocity approach to be used on problems with structural interfaces, and preliminary results have shown improved accuracy over Nastran and finite difference. The method's practical application is demonstrated on a wing panel model. | |
| 18:15 | 18:45 | 0125 |
Aeroelastic tailoring of composite lifting surfaces based on high-fidelity models E. Caligari, Alma Mater Studiorum, University of Bologna, IT; D. Zamani, Politecnico di Torino, IT This work seeks to perform single and multi-objective optimization of composite wings, modeled as thin plates, by means of a high order aeroelastic model based on the Carrera Unified Formulation and the Doublet Lattice Method. Simulations are performed to maximize the flutter speed by considering the divergence constraint too; both surrogate models and genetic algorithms are adopted. |
| 3.13 Tu, 16.6. 16:45 - 18:45 | Wind Tunnel and Flight Testing 3 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 16:45 | 17:15 | 0260 |
Wind tunnel aeroelastic analysis of a low-stiffness wing at high angles of attack and low Reynolds numbers M. Dagilis, Kaunas university of technology, LT This paper describes the results of a wind tunnel aeroelasticity study conducted in aerodynamically non-linear conditions. Such experimental data is required for the development of fast aerodynamically non-linear aeroelasticity models, whereas most currently used models use linear aerodynamics. These models could be used for better control law design at the edges of an aircraft's flight envelope. | |
| 17:15 | 17:45 | 0275 |
Experimental Study of Nonlinear Aeroelastic Response in a Highly Flexible Wing Configuration L.-M. Marchetti, University of Bristol, GB The experimental data obtained in this campaign will provide a valuable benchmark for the validation of nonlinear aeroelastic models targeting highly flexible lifting surfaces. In addition, the dataset will contribute to improved understanding of mass distribution effects on flutter behaviour in swept flexible wings. The results will also inform future design strategies for large deformations aeroelastic experiments. | |
| 17:45 | 18:15 | 0243 |
AEROELASTIC MODEL UPDATE FOR A FLEXIBLE WING USING EXPERIMENTAL DATA G. Stavorinus, TU Berlin, DE This work presents a methodology for updating the aeroelastic models of flexible aircraft wings for use in Nastran and Loads Kernel simulations using experimental wing root load measurements obtained from wind tunnel tests. The procedure is validated using static and dynamic experimental measurements from the TU-Flex flexible wing. Updated models show good agreement with experimental data. | |
| 18:15 | 18:45 | 0079 |
Experimental Body Freedom Flutter Test Campaign of Aeroelastically Scaled X-56 Wing K. McHugh, US Air Force Research Laboratory, US AFRL’s new wind tunnel pitch-plunge mount and X-56 wing model demonstrate a new design, print, and test paradigm for aeroelastic models with rigid body dynamics. The wing is aeroelastically scaled to tunnel dimension using sizing optimization techniques, 3D printed, scanned for geometric accuracy, shaker tested for modal data, and tunnel tested to validate body freedom flutter analyses. |
| 3.14 Tu, 16.6. 16:45 - 18:45 | Active Control and Adaptive Structures 1 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 16:45 | 17:15 | 0068 |
Structural Blending for Active Flutter Suppression J. Eichelsdörfer, DLR, DE An active flutter suppression controller is presented. Accelerometer signals and dually control surface deflections are linearly combined to isolate the critical structural eigenmodes. A low-order structured H-Infinity controller is synthesized. Relative to H-2-optimal blending, this approach achieves increased damping and reduced control effort. Open-source MATLAB code accompanies the paper. | |
| 17:15 | 17:45 | 0191 |
Adaptive Control Law for Active Flutter Suppression in Presence of Actuation Failure E. Roncolini, Politecnico di Milano, IT An adaptive active controller for flutter suppression, capable to detect actuation failure and re-allocate the workload on the functioning control surfaces by means of adaptive methodology will be studied in this work, ensuring fault tolerant flutter suppression, when sufficient redundancy is present in the control surfaces. | |
| 17:45 | 18:15 | 0301 |
Hybrid Robust Incremental Nonlinear Control with Guaranteed Disk Margins and Flight Quality for Aeroelastic Aircraft T. Zhang, TU Delft, NL With increasing aspect ratios and composite usage in commercial aircraft, aeroelastic challenges are intensifying. Active control offers a solution for trajectory tracking and load alleviation, yet existing methods lack systematic guarantees for robust stability and flight performance. This paper proposes a hybrid framework combining Incremental Nonlinear Dynamic Inversion (INDI) with mu-synthesis. INDI manages nonlinearities and reduces model dependency, while mu-synthesis optimizes gains for robust stability. A key contribution is the explicit guarantee of disk margins by taking the advantage of existing disk-like perturbation analytical from. The disk-like perturbations are direcly used as linear uncertainty blocks. using this, we directly embeded the robust requirements in the control synthesis and enables the use of efficient linear robust optimization, avoiding complex nonlinear approaches and overcoming the reliance on a posteriori verification common in state-of-the-art methods. Furthermore, the framework incorporates a systematic tuning strategy for flight performance and handling qualities. Validated on a high-aspect-ratio free-flying aeroelastic aircraft model, the proposed approach achieves simultaneous trajectory tracking and gust load alleviation, strictly satisfying stringent flying quality and robustness stability requirements. | |
| 18:15 | 18:45 | 0235 |
Application of Udwadia-Kalaba method to flared folding wing tips: a low order explicit model for numerical continuation J.H. Ascham, University of Bristol, GB Folding wing tips, deployable in-flight, aid gust loads alleviation and roll control. Prior models use linear simplifications or high-order DAEs unfit for continuation. This work applies Udwadia-Kalaba multibody dynamics for minimal state ODEs, validated vs. ANCF and experiments. Coupled to unsteady lifting line, bifurcation analysis agrees well with data, enabling broad stability assessment. |
| 3.15 Tu, 16.6. 16:45 - 18:45 | High Altitude Platform (HAP) Chair: N.N. | ALTE MENSA - Room Taberna |
| 16:45 | 17:15 | 0014 |
HAP-alpha: Model Updating Based on Ground Vibration Test and the Influence on Loads and Aeroelasticity A. Voß, DLR - Institute of Aeroelasticity, DE This paper presents the results of the ground vibration test (GVT) of the HAP-alpha configuration and a comparison with the structural modeling using finite elements (FE). The following questions are adressed: How good/reliable was the FE model? What is the influence of the GVT on loads? Does the updated model lead to any restrictions w.r.t. the initial design? | |
| 17:15 | 17:45 | 0276 |
HAP-alpha: Ground Vibration Test of the Ultra-Lightweight High-Altitude Platform Structure C. Thiem, DLR Goettingen, DE In April 2025, the DLR Institute of Aeroelasticity conducted a ground vibration test on the High Altitude Platform HAP-alpha. This paper discusses the challenges of suspending such an ultra-light structure and measuring the acceleration responses at the resulting low eigenfrequencies. | |
| 17:45 | 18:15 | 0210 |
HAP-ALPHA: FLIGHT CONTROL DESIGN CONSIDERING STRUCTURE AND RIGID-BODY COUPLING C. Weiser, DLR Institute of Flight Systems, DE Flight?control law development generally consists of separate processes for primary flight control development and (gust) load alleviation. Lightweight UAVs like the German Aerospace Center’s "HAP-alpha" lack this separation, as rigid body and flexible modes overlap. This paper proposes using a single flight control design which considers both aspects based on a flexible aircraft model. | |
| 18:15 | 18:45 | 0129 |
HAP-ALPHA: DEVELOPMENT OF SYSTEM IDENTIFICATION MANOEUVRES FOR LOW-ALTITUDE FLIGHT TESTING OF A FLEXIBLE HAP Y. J. Hasan, DLR - German Aerospace Center, DE This paper develops low-altitude system identification manoeuvres for flexible high-altitude platform aircraft. It presents the basic manoeuvre design, the assessment of the resulting flight quantities and loads and the generation of virtual flight test data. A final system identification shows the manoeuvres’ general feasibility for obtaining adequate aircraft rigid-body and flexible parameters. |
| Tu, 16.6. 18:45 - 18:46 | End of IFASD 2026 | Day 1 | 18:45 - 18:46 | ||||||
| Tu, 16.6. 19:30 - 22:30 | Reception@Altes Rathaus | 19:30 - 22:30 | ||||||
| We, 17.6. 08:00 - 08:30 | Registration opens | 08:00 - 08:30 | ||||||
| 0.2 We, 17.6. 08:30 - 09:15 | Plenary 2 Chair: L. Tichy, German Aerospace Center, DE | |||
| 08:30 | 09:15 |
Aeroelastic certification with EASA: Methods, challenges and lessons learnt Elena García Sánchez; European Union Aviation Safety Agency | ||
| We, 17.6. 09:15 - 09:30 | Room Change | 09:15 - 09:30 | ||||||
| 4.11 We, 17.6. 09:30 - 11:00 | Aeroelasticity in Conceptual Aircraft Design 4: Unconventional Configurations (2) Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 09:30 | 10:00 | 0107 |
COMPUTATIONAL FRAMEWORK FOR DYNAMIC LOADS ANALYSIS OF THE JOBY EVTOL AIRCRAFT M Castellani, Joby Aviation, US This paper presents the computational framework that has been implemented at Joby Aviation for dynamic loads analyses. The computational framework presented integrates various elements from commonly used methods and tools in structural dynamics and aerodynamics, to build a comprehensive tool that allows performing dynamic loads analyses, such as gust response, oscillatory surface failures, dynamic landing. | |
| 10:00 | 10:30 | 0059 |
Movable Layout Optimisation of a Prandtl-Plane S de Boer, TU Delft, NL This paper will present the movable layout optimisation of a box-wing aircraft, such as a Prandtl-Plane. The optimised movable layout for handling qualities and load alleviation is not yet well understood. Hence, the effect of different load alleviation techniques and flight dynamic control on the movable layout will be investigated using the continuous movable parameterisation methodology. | |
| 10:30 | 11:00 | 0164 |
Aerodynamic Characteristics Analysis of Bio-inspired Flying Fish Membrane Wings Considering Static Aeroelastic Effects M. Zhou, School of Aeronautic Science and Engineering, Beihang University, CN Fluid-structure interaction analyses are conducted on the three-dimensional membrane wings, bio-inspired by the flying fish pectoral fin. A strongly coupled algorithm based on the predictor-corrector method is developed to investigate the effects of the supporting skeleton and structural stiffness on their aerodynamic characteristics and deformation responses. |
| 4.12 We, 17.6. 09:30 - 11:00 | Computational Aeroelasticity 4 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 09:30 | 10:00 | 0224 |
TAIL BUFFETING OF A FLEXIBLE WING IN TRANSONIC FLOW K.V. Venkatraman, Indian Institute of Science, IN Vertical and horizontal tail buffeting is critical during moderate and high angle-of-attack (AOA) maneuvers of a flexible combat aircraft. Tail buffeting refers to the vertical and, or, horizontal tail or fin vibrating due to the excitation caused by highly vortical flows emanating from the fore-body of the aircraft including the nose/intake/canard/wing at high AOA. Unsteady transonic flow over the trapezoidal wing planform with horizontal and vertical tail is analyzed at Mach 0.8 using RANS and URANS solvers. The fluid solver is coupled with the structural dynamics of the airframe obtained from a finite element solver. This paper analyzes the vortex breakdown and its effect on tail buffeting at different angles of attack. The influence of horizontal and vertical tail dynamic stiffness on alleviating tail buffeting is also studied. | |
| 10:00 | 10:30 | 0118 |
Investigation of Buffet and Buffeting Characteristics in Benchmark Supercritical Wing Considering Aeroelastic Effects Y.-M. Zhang Zhang, Beihang University, CN This study reveals that prescribed modal motions effectively attenuate transonic buffet on elastic wings. Additionally, a forced vibration method is validated, predicting buffet response within 10% accuracy of full fluid-structure coupling while reducing computational cost by over 60%, offering significant efficiency for industrial applications. | |
| 10:30 | 11:00 | 0302 |
Development of the first-principles Adaptive Euler methodology to FSI and buffeting Johan Jansson, KTH, SE We describe the Adaptive Euler methodology, and a fluid-structure interaction (FSI) development, together with supporting validation of buffeting from the Aeroelastic, Drag and High Lift Prediction Workshops and industrial results. Our proposed FSI methodology includes both a general Immersed Unified Continuum variant, as well as a simpler partitioned variant iterating between fluid and structure. |
| 4.13 We, 17.6. 09:30 - 11:00 | Wind Tunnel and Flight Testing 4 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 09:30 | 10:00 | 0013 |
Experimental Investigation of Whirl Flutter Stability and Propeller Aerodynamic Derivatives J. Cecrdle, VZLU AEROSPACE, CZ This paper deals with the recent accomplishment in the testing of the W-WING demonstrator. It includes outline on the theoretical background, demonstrator concept and preparatory tests. The focus is paid on the WT measurements including the measurements of stability and propeller aerodynamic derivatives. It presents the tests arrangements, methodologies, configurations and the examples of results. | |
| 10:00 | 10:30 | 0092 |
Experimental Investigation of Vertical Tail Buffeting on a Triple-Delta-Wing Configuration in Transonic Flows P. Hartl, German Aerospace Center (DLR), Institute of Aeroelasticity, DE Vertical tail buffeting of modern, high-agility, multi-delta-wing aircraft is investigated on the DLR-F23-T wind tunnel model under flight-relevant Mach numbers, considering different vertical tail dihedral angles (28°/45°) and material properties (quasi-rigid/flexible). Vortex breakdown causes a reduction in total lift and strong structural vibrations of the vertical tail with buffet onset. | |
| 10:30 | 11:00 | 0038 |
Mach 6 Aerothermoelastic Experiment with Shock Impingement on a Compliant Panel under Thermal and Mechanical Buckling D. O. Kirkpatrick, The University of New South Wales, AU This study consists of wind tunnel experiments conducted to more fully understand the underlying mechanisms of the interactions between aerodynamic, thermal and mechanical loads on a compliant, buckled structure in Mach 6 flow. This study's contributions expand the FTSI and SBLI knowledge base and provide a database that could help validate high-speed simulations and inform vehicle design. |
| 4.14 We, 17.6. 09:30 - 11:00 | Active Control and Adaptive Structures 2 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 09:30 | 10:00 | 0161 |
ACTIVE WING FOR FUTURE REGIONAL AIRCRAFT: MORPHING STRUCTURES AND AEROELASTIC CONTROL F. Toffol, Politecnico di Milano, IT Within Clean Aviation, Politecnico di Milano develops integrated technologies for an intelligent, active wing for future regional aircraft. HERWINGT and HERA combine morphing ailerons, gust load alleviation and active flutter suppression, with different control laws tested in wind tunnels to improve efficiency, weight and aeroelastic performance. | |
| 10:00 | 10:30 | 0158 |
EXPERIMENTAL TESTING OF A HIGH-BANDWIDTH MORPHING AILERON FOR A HYBRID ELECTRIC REGIONAL AIRCRAFT A. De Gaspari, Politecnico di Milano, IT This paper presents the experimental validation of an innovative morphing aileron for a hybrid-electric regional aircraft. Ground and wind tunnel tests are aimed at assessing functionality, shape accuracy, actuation loads, bandwidth and aerodynamic performance, to demonstrate the potential of the device for reduced drag, lower actuation forces and active load control capabilities. | |
| 10:30 | 11:00 | 0254 |
Experimental characterisation of prototype wing for reflexed airfoil morphing P Georgopoulos, Delft University of Technology, Faculty of Aerospace Engineering, NL Experimental results demonstrate the aerostructural performance of a prototype wing for reflexed airfoil morphing. Wind tunnel testing validates the reflexed airfoil morphing functionality at large scale. The effect of asymmetric morphing between flaps on the wake velocity deficit is investigated, indicating how a seamless transition between flaps outperforms a discontinuous transition. |
| 4.15 We, 17.6. 09:30 - 11:00 | High frequency Structural Dynamics & Impacts Chair: N.N. | ALTE MENSA - Room Taberna |
| 09:30 | 10:00 | 0213 |
SURVEY OF AVIATION BIRD STRIKE HAZARD AND ITS NUMERICAL SIMULATION H Climent, UC3M, ES According to FAA, “eighty-one strikes resulted in a destroyed aircraft from 1990-2022 (none in 2022); 46 (57 percent) of these occurred at general aviation airports. The annual cost of wildlife strikes to the USA civil aviation industry in 2022 was projected to be 67,848 hours of aircraft downtime and $385 million in direct and other monetary losses” [01]. These 81 aircraft lost were only in the US. The probability of a bird strike per flight hour has multiplied by 3 in the last 30 years and the increase trend will continue in the future. Similar aircraft loses and impact trends have been reported in Europe by EASA, in China and also in the available military aircraft databases. This paper presents a survey of more than 150 references, papers, books and reports, covering the many different aspects of the bird strike problem and analysing the alternatives for its numerical simulation. The authors conclude that by using the explicit Finite Element Method (FEM) technique combined with Smoothed Particle Hydrodynamics (SPH) modelled birds the problem can be simulated today with suitable accuracy at a reasonable cost, although other alternatives and promising new methods will be also presented. In addition to the references reviewed, the authors present sensitivity analysis and results based on their own simulations and the test data from various sources used for validation of models (bird, material characteristics, specimens, etc). The strain rate effect in tension cases that will be shown in the paper has not been addressed so often in the literature like the compression cases…The final part of the paper will address the stochastic approach needed to properly assess the margin in presence of uncertainties. | |
| 10:00 | 10:30 | 0215 |
Vibroacoustic computation of a business aircraft fuselage area C Rousset, Dassault Aviation, FR The final paper will describe the vibro-acoustic computation strategy of Dassault Aviation and its application on a scale one case. First, some theory of the vibro-acoustic issue will be given, then the modelled system will be described with a focus on the poro-elastic material, the excitation field and the equations governing the propagation and radiation and finally some visualization of the results and comparisons with experimental data will be provided. | |
| 10:30 | 11:00 | 0103 |
HIGH-RATE TESTING AND MODELLING OF AEROSPACE LAP-SHEAR FASTENER JOINTS USING A SPLIT HOPKINSON TENSION BAR F Larsson, Luleå university of technology, SE This work introduces a novel double-sided Split Hopkinson Tension Bar approach to characterise high-rate tensile behaviour of aerospace lap-shear fastener joints. Combined with LS-Dyna simulations, it reveals key dynamic force-transfer and failure mechanisms, enabling more accurate impact modelling and safer, lighter aircraft structures. |
| Coffee Break | 11:00 - 11:30 | |||||||
| 5.11 We, 17.6. 11:30 - 13:00 | Aeroelasticity in Conceptual Aircraft Design 5: Supersonic Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 11:30 | 12:00 | 0104 |
Low-Order Multidisciplinary Modeling of Hypersonic Vehicles with Coupled Aeroelastic and AeroâPropulsive Effects R. Silva, Aeronautics Institute of Technology, BR This work presents a low-order multidisciplinary framework for hypersonic vehicles that explicitly couples aeroelasticity, propulsion, and flight mechanics at the conceptual design stage. Results show that structural flexibility significantly affects trim, stability, and aero–propulsive interaction, demonstrating the necessity of integrated low-order models for early hypersonic vehicle design. | |
| 12:00 | 12:30 | 0120 |
AEROTHERMOELASTIC COUPLING EFFECTS ON SUPERSONIC AIRCRAFT FLIGHT DYNAMICS G. Z. Wang, Beihang University, CN Supersonic aircraft face severe aerothermoelastic coupling. This study proposed a unified aerothermoelastic-flight dynamics analysis method and applied it to a missile model. Results revealed that elastic and thermal effects strongly impact flight dynamics and stability, and proved that the method is efficient for flexible supersonic aircraft analysis under aerodynamic heating. | |
| 12:30 | 13:00 | 0105 |
PRELIMINARY STRUCTURAL DESIGN TOOL FOR FLEXIBLE SLENDER BODIES WITH AEROELASTIC CONSTRAINTS Y. Karniel, Technion -- Israel Institute of Technology, IL This work presents a computationally efficient preliminary design tool addressing the gap in static aeroelastic analysis for flexible slender bodies. The computationally efficient approach achieves acceptable accuracy versus commercial tools. It Demonstrated 30% mass reductions meeting stability requirements, enabling both parametric studies and automated optimization during conceptual design. |
| 5.12 We, 17.6. 11:30 - 13:00 | Steady/Unsteady Aerodynamics 1 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 11:30 | 12:00 | 0138 |
A time-domain panel method for unsteady subsonic compressible aerodynamics D. Wen, Beihang University, CN A time-domain compressible panel method is proposed based on the compressible potential flow equation, and the wake model is improved to address the time-delay characteristics and wake interference. Three cases further demonstrate its accuracy, along with its advantages in gust aerodynamic force calculation, wake interference calculation and co-simulation with nonlinear structural models. | |
| 12:00 | 12:30 | 0273 |
INVESTIGATION OF A VORTEX-BASED THREE-DIMENSIONAL CORRECTION FOR UNSTEADY EFFECTS IN THE ACTUATOR LINE METHOD V.G. Kleine, Instituto Tecnológico de Aeronáutica, BR The Actuator Line Method (ALM) models lifting surfaces in CFD using airfoil data, allowing coarser grids and lower simulation cost. With longer, flexible wind turbine blades, ALM is key for aeroelastic studies. This work proposes a vortex-based unsteady correction to 3D ALM, reducing mesh dependency and improving unsteady loads, validating it against theory and doublet lattice method. | |
| 12:30 | 13:00 | 0313 |
A Multi-Fidelity Neural Network Framework for Enhancing Strip-Theory Aerodynamics V Santos, Instituto Tecnológico de Aeronáutica, BR We present a physics-consistent, multi-fidelity neural-network surrogate that blends CFD, wind-tunnel data, and strip-theory to accurately predict aerodynamic loads with low computational effort. The model enables fast, reliable simulations of flexible aircraft, supporting future applications in real-time control and design. |
| 5.13 We, 17.6. 11:30 - 13:00 | Wind Tunnel and Flight Testing 5 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 11:30 | 12:00 | 0101 |
Continuous Online Monitoring of Aeroelastic Modal Parameters: A Comprehensive Study of Wind Tunnel and Flight Tests R. Volkmar, DLR, DE This work demonstrates applications of online aeroelastic monitoring in wind tunnel and flight tests. It proves the method to enhance flight test safety, data exploitation, and performance. Advantages are highlighted over offline methods and limitations for future improvements are identified. Key contribution: validated transferability from wind tunnel to flight environments. | |
| 12:00 | 12:30 | 0241 |
GROUND EXPERIMENTAL TESTS AND FLIGHT TEST DESIGN FOR A FLEXIBLE AIRCRAFT FLYING DEMONSTRATOR P. G. González, TU-Berlin, DE This work presents a bottom-up validation approach and flight test preparation strategy for a flexible aircraft demonstrator. Full vehicle structural updates, ground vibration testing, inertia measurements, and staged flight tests ensure accurate aeroelastic and flight dynamic models, enabling a safer first flight test campaign. | |
| 12:30 | 13:00 | 0044 |
The X-59 Journey to Aeroelastic Airworthiness Clearance N. S. Spivey, NASA Armstrong / Aerostructures Branch, US The X-59 aircraft is a collaboration between Lockheed Martin (LM) & NASA to demonstrate sonic boom reductions enabled by aerodynamic shaping. To safely fly X-59, LM & NASA structural dynamics engineers developed FEMs, completed numerous flutter & aeroservoelasticity analyses, and conducted several structural ground tests. This paper describes X-59’s journey to aeroelastic airworthiness clearance. |
| 5.14 We, 17.6. 11:30 - 13:00 | Aeroservoelasticity 3 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 11:30 | 12:00 | 0078 |
EIGENVALUE SENSITIVITY ANALYSIS FOR AEROSERVOELASTIC CONTROL CO-DESIGN N Joanow, University of Pittsburgh, US Efficient gradient-based aeroservoelastic optimization is demonstrated using analytical eigenvalue sensitivity analysis for Riccati-based controllers. Applied to a flexible wing, this achieves 35% mass reduction while maintaining flutter stability, with lower computational cost than finite-difference methods, facilitating integration of active flutter suppression into early-stage aircraft design. | |
| 12:00 | 12:30 | 0200 |
High-Dimensional Bayesian Control Co-Design Optimisation For Constrained Aeroelastic Tailoring Of Flexible Aircraft J.R. van Zyl, Delft University of Technology, NL Control Co-Design Optimisation (CCDO) is applied to the aeroelastic tailoring problem through an LQR and Autoencoder-Enhanced Joint Dimensionality Reduction for Constrained-Bayesian Optimisation (AERO-BO) to enable high-dimensional global optimisation. The design yields a lighter wing than that from sequential design. This is the first application of Bayesian CCDO for aeroelastic tailoring. | |
| 12:30 | 13:00 | 0049 |
Tailoring of Shock Dynamics for Improved Transonic Flutter Performance K. Patel, University of Cambridge, GB The unsteady transonic flow around a pitching airfoil is shown to be analagous to the 1D flow through a choked nozzle with a time-varying throat area. Analytical solutions for the 1D nozzle thus identify the physical mechanisms that govern the shock dynamics during flutter. This allows the shock motion to be related to the frequency of oscillation and the airfoil's aerodynamic design. |
| 5.15 We, 17.6. 11:30 - 13:00 | Rotorcraft Aeroelasticity 1 Chair: N.N. | ALTE MENSA - Room Taberna |
| 11:30 | 12:00 | 0087 |
NONLINEAR AEROELASTIC ANALYSIS OF ROTOR-STRUCTURE INTERACTION WITH PITCH-YAW FREEPLAY D. T. Tripathi, University of Bristol, GB This paper presents a comprehensive numerical investigation of the nonlinear dynamics of newly developed Bristol Whirl Flutter Rig (BWFR), designed for experimental testing in a Vertical Wind Tunnel. The analysis focuses on the role of freeplay nonlinearity in the pitch and yaw degrees of freedom, which introduces discontinuities in stiffness and fundamentally changes the aeroelastic response. | |
| 12:00 | 12:30 | 0089 |
EXPERIMENTAL INVESTIGATION OF NONLINEAR WHIRL-FLUTTER IN A 2-DOF ROTOR-PYLON SYSTEM Y. Qiu, University of Bristol, GB This work presents one of the first detailed experimental studies of nonlinear whirl-flutter in a 2-DoF rotor–pylon system. Beyond linear onset, we identify stable and unstable limit-cycle oscillations and subcritical behaviour through wind-tunnel tests with dual-axis high-resolution sensing. The results provide new insight for modelling post-onset aeroelastic dynamics in rotorcraft systems. | |
| 12:30 | 13:00 | 0292 |
Comparative Aeroelastic Analysis of Distributed Electric Propulsion Wings Y. E. Dogru, Gebze Technical University, TR This research investigates coupled aeroelastic dynamics of flexible wings with distributed propellers using quasisteady, frequency-domain (Theodorsen), and time-domain (Wagner) aerodynamics. Results show wing-dominated flutter governs critical speeds; forward whirl modes transition to wing instabilities, while backward whirl appears at higher velocities—critical for eVTOL stability design. |
| Networking Lunch & Poster Session | 13:00 - 14:15 | |||||||
| 6.11 We, 17.6. 14:15 - 16:15 | Reduced Order Modelling 1 Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 14:15 | 14:45 | 0114 |
Data-driven prediction of aerodynamic loads on flexible wings combining neural-networks and low-dimensional projections N. Fabbiane, DAAA, ONERA, FR This contribution introduces a data?driven surrogate that merges low?dimensional linear projections with a compact neural?network for the prediction of aerodynamic loads on the surface of a deformable wing. The balanced nature of the encoder/decoder preserves the input?output coupling between the pressure and deformation fields at the surface, while allowing for reliable and rapid predictions. | |
| 14:45 | 15:15 | 0297 |
A RESIDUAL LEARNING FRAMEWORK FOR IMPROVED AERODYNAMIC LOAD PREDICTION E. S. Cesnik, University of Michigan, US This work presents a novel framework that integrates a baseline aerodynamic model based on linear steady aerodynamic model with data-driven residual corrections. By decomposing total loads into a physics-based baseline and effect-specific residuals, it improves unsteady and nonlinear aerodynamic load prediction accuracy and interpretability. | |
| 15:15 | 15:45 | 0116 |
Neural Ordinary Differential Equations for Transonic Buffet Reduced-Order Modeling in Aeroelasticity M. J. Candon, RMIT University, AU Physics-guided Neural ODE ROM for transonic buffet aeroelasticity: Rayleigh oscillator + finite-memory Volterra forcing + neural residual learned from CFD. Captures aeroelastic response, including high-amplitude LCO, with orders-of-magnitude speedup for design studies, control and uncertainty quantification. | |
| 15:45 | 16:15 | 0251 |
Aeroelastic data-assimilation of wing tunnel experiments using aerodynamics reduced order models P.-E. des Boscs, ONERA, FR We present a data-assimilation framework that reconstructs full wing displacement and pressure fields from partial measurements by coupling data assimilation using a structural model only with aerodynamic ROM. Applied to a flexible composite wing, it recovers displacements and pressure fields without flow adjoint computations, enabling rapid aeroelastic analysis and experimental data interpretation. |
| 6.12 We, 17.6. 14:15 - 16:15 | Steady/Unsteady Aerodynamics 2 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 14:15 | 14:45 | 0024 |
Buffet onset prediction with the linearized frequency-domain method D. Quero, DLR, DE A new method for predicting transonic buffet onset is based on linearized frequency-domain CFD and a Loewner-based state-space realization of the unsteady aerodynamics. Physically unstable fluid poles are filtered by a residue-based metric, yielding a compact model that predicts buffet onset efficiently and can be integrated into existing industrial aeroelastic workflows. | |
| 14:45 | 15:15 | 0046 |
Assessment of machine learning methods for the prediction of aircraft buffet loads G. Grasso, Airbus Defence and Space GmbH, DE The prediction of buffet loads and of sound emission generated by the unsteady pressure over lifting surfaces is a major challenge in aircraft design. A machine learning model of the unsteady pressure field over a wing is implemented by means of an autoencoder and a recurrent neural network. This allows to predict the pressure field with correct statistics and at very low computational cost. | |
| 15:15 | 15:45 | 0299 |
EFFICIENT NONLINEAR GUST LOAD PREDICTION VIA A STATE-SPACE LIFTING LINE WITH NON-ITERATIVE HIGH-FIDELITY CORRECTION E. Grau Lozano, Airbus, FR This study proposes an enhanced State-Space Lifting Line method for nonlinear gust prediction on High-Aspect-Ratio Wings. Integrating a non-iterative, in-the-loop high-fidelity correction, it is validated on the XRF1-HARW against CFD. Results demonstrate superior peak load accuracy over linear methods, providing an efficient time-domain tool for flexible aircraft design. | |
| 15:45 | 16:15 | 0063 |
Validation of Aeroelastic Aspects of new CFD Solver CODA with AEROSTABIL Windtunnel Experiment J. Noel, Airbus, DE The work validates the new RANS-CFD solver CODA against the AEROSTABIL windtunnel experiment, demonstrating new possibilities in the field of aeroelasticity with the new tool. Using LFD, the study compares aerodynamic pressures and flutter boundaries for different turbulence models. It also validates nonlinear aerodynamic effects which lead to limit cycle oscillations with time-domain simulation. |
| 6.13 We, 17.6. 14:15 - 16:15 | Computational Aeroelasticity 5 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 14:15 | 14:45 | 0025 |
CFD-BASED FLUTTER ANALYSES OF THE AWI HIGH-ASPECT-RATIO WING CONFIGURATION R. Thormann, Airbus Operations, DE A very flexible high-aspect-ratio wing is analyzed with special emphasis on nonlinear structures and their effect on aeroelastic stability. While focussing on low Mach numbers, CFD-based aerodynamics are used, especially to account for in-plane motion. The effect of preloaded structures resulted in a more complex flutter process. Sensitivities are presented and comparison to W/T data shown. | |
| 14:45 | 15:15 | 0186 |
NUMERICAL VALIDATION OF ACTUATOR LINE METHOD FOR SUBCRITICAL FLUTTER PREDICTION A.-A. García Quesada, Technical University of Berlin, DE This work assesses the capability of ALM to capture subcritical flutter in a typical section. Coupled with plunge and pitch dynamics, ALM will be uised to predict flutter onset, post-flutter limit cycles, and bifurcation behavior. Benchmarking against reference results demonstrates its potential as a computationally efficient tool for nonlinear aeroelastic analysis and early-stage aircraft design. | |
| 15:15 | 15:45 | 0209 |
GEOMETRICALLY NONLINEAR AEROELASTIC CHARACTERISTICS OF WINGLETS FOR PASSIVE MORPHING WING APPLICATIONS M.N.-A. Kouchlef, The University of Tokyo, JP This work extends the geometrically nonlinear aeroelastic stability analysis of adaptive winglets to fully 3D geometry and flow. Using a validated VLM/UVLM-based framework, it reveals the impact of passive morphing and winglet design on flutter and divergence phenomena. | |
| 15:45 | 16:15 | 0029 |
Aeroelastic Stability Analysis of Wing-Multi-Propeller Systems Under Aerodynamic Interactions Using the UVLM J. Santos, University of São Paulo, BR Wing-multi-propeller systems may exhibit aeroelastic instabilities such as wing and whirl flutter. The flutter boundary of these configurations are sensitive to aerodynamic interference effects. This work quantifies 3D aerodynamic versus interference effects and evaluates the unsteady vortex-lattice method as a potential-flow alternative, advancing modeling capabilities for the scientific community. |
| 6.14 We, 17.6. 14:15 - 16:15 | Ground Vibration Testing of Flight Vehicles Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 14:15 | 14:45 | 0185 |
Exploring new technical environment for Ground Vibration Test for the eXtra performance WING Airbus UpNext project N. LASTERE, AIRBUS SAS, FR Performing a Ground Vibration Test is a key enabler for First Flight to secure the flight envelope opening, especially on a new aircraft prototype featuring innovative technical solutions for active and passive vibration and load alleviation. This paper is describing the specificities for such a complex GVT and the implemented testing set-up involving three testing teams of Airbus, DLR & ONERA | |
| 14:45 | 15:15 | 0080 |
Automatic Phase Resonance Testing of Airbus eXwing Aircraft for Flutter Computation Updating A CHUKWU, ONERA, FR An automatic phase resonance method is developed to facilitate ground vibration test (GVT) of aircraft structures. As an extension of the phase-locked loop method (PLL), which is a recent technique in nonlinear structure identification, it is well adapted to complex systems. The extended algorithm exploits the complex power to minimize the mean phase deviation (MPD) of the response signals. | |
| 15:15 | 15:45 | 0246 |
EXPERIMENTAL AND OPERATIONAL MODAL ANALYSIS OF FULL-SCALE AIRCRAFT GVT: TOWARDS A HYBRID METHODOLOGY C.G.-T Casillas Gil, Airbus Defence and Space, ES Experimental Modal Analysis (EMA) in the framework of Ground Vibration Tests (GVTs) is traditionally used to identify reliable normal modes with measured input excitation forces. Additionally, Operational Modal Analysis (OMA) can be also used for a similar purpose when no input force control is available. This paper seeks to assess the differences between EMA and OMA for a complete aircraft GVT. | |
| 15:45 | 16:15 | 0165 |
DESIGN AND GROUND VIBRATION TESTING OF AN EXTERNAL DROP-TANK FOR FUEL SLOSH STUDIES ON A DYNAMICALLY SCALED DELTA WING A. Ellmo, Saab AB, SE This article details the design, manufacture and initial testing of a slosh tank model, coupled with a wing from the dynamically scaled NASA-KTH transonic flutter model. The results suggest that the presence of a liquid payload with a free surface impacts the aeroelastic stability boundaries, mainly through increased separation of the wings bending and torsional modes. |
| 6.15 We, 17.6. 14:15 - 16:15 | Rotorcraft Aeroelasticity 2 Chair: N.N. | ALTE MENSA - Room Taberna |
| 14:15 | 14:45 | 0220 |
CFD-Based Identification of Motion-Induced Airloads on a Rotor Configuration in Hover and Forward Flight C. Kaiser, DLR (German Aerospace Center), Institute of Aeroelasticity, DE The present study addresses the identification of motion-induced airloads on a rotary-wing configuration using high-fidelity CFD in hover and forward flight. The goal is to determine the harmonic transfer function matrix of the aerodynamic forces enabling coupling with the structural model in the Laplace domain. | |
| 14:45 | 15:15 | 0226 |
The effect of vortex ring state on aeroelasticity of rotor blades M.A. Amoozgar, University of Nottingham, GB This paper investigates the effects of vortex ring state on the aeroelastic stability and response of rotor blades in descent flight. The aeroelasticity of the rotor blade is modelled by coupling a two-degree of freedom flap-pitch system with an unsteady strip theory model. The VRS inflow model is based on the correction and extension of the momentum theory to eliminate the singularities. | |
| 15:15 | 15:45 | 0253 |
Influence of Geometric Nonlinearities on Inverse Load Identification for Helicopter Rotor Blades L. Kettenhofen, Institute of Structural Mechanics and Lightweight Design, RWTH, DE This work evaluates the importance of accounting for geometric nonlinearities for accurate inverse load identification of helicopter rotor blades. The findings highlight a significant gap in current research and underscore the need for advanced methods to improve inverse load identification in the framework of operational in-flight monitoring systems. | |
| 15:45 | 16:15 | 0194 |
EXPERIMENTAL INVESTIGATION AND AEROELASTIC CHARACTERISATION OF A MULTIROTOR SYSTEM T Sharma, University of Bristol, GB This paper presents the evolution of experimentally identified modal properties under varying loads. The analysis reveals the influence of aerodynamic loading on complex interactional phenomena, including modal veering and whirling modes. Finally, it provides initial experimental insights into the stability of the coupled dual-rotor system. |
| Coffee Break | 16:15 - 16:45 | |||||||
| 7.11 We, 17.6. 16:45 - 18:45 | Reduced Order Modelling 2 Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 16:45 | 17:15 | 0264 |
Parametric Volterra Series for Flutter Analysis M Righi, ZHAW, CH This study presents an analysis and reflection on the use of data-driven nonlinear, parametric aerodynamic Reduced-Order Models for flutter analysis, with particular emphasis on Volterra kernels. While errors are introduced during model generation, the approach significantly reduces overall costs and makes a number of evaluations possible. AI/ML tools are likely to further improve the situation. | |
| 17:15 | 17:45 | 0156 |
DEVELOPMENT OF STRUCTURAL REDUCED ORDER MODEL FOR MODAL BASE AEROELASTIC SOLVERS VIA GLOBAL OPTIMIZATION O. Köse, HSB Solutions GmbH, DE This study presents a global-optimization-based methodology to generate high-fidelity beam stick models of complete aircraft. Using a multi-objective modified Crow Search Algorithm, the approach correlates modal properties, flutter characteristics, and gust responses of reduced-order models with 3D GFEM results, achieving high accuracy with significantly reduced computational cost. | |
| 17:45 | 18:15 | 0240 |
ON THE FLUTTER MECHANISM DRIVEN BY SECOND BENDING-FIRST TORSION COUPLING IN HIGH-ASPECT RATIO WINGS M. Pirnay, University of Liège, BE This work investigates flutter mechanisms in high-aspect-ratio wings, focusing on second-bending–first-torsion (B2–T1) coupling. A reduced-order aeroelastic model, validated experimentally, reveals a non-monotonic damping “hump” behavior driven by modal energy transfer and spanwise redistribution of aerodynamic work, highlighting the role of higher-order modal interactions. | |
| 18:15 | 18:45 | 0021 |
Benchmark Supercritical Wing Computations Using CREATE-AV KESTREL and NASA AEROM W. A. Silva, NASA, US The Benchmark Supercritical Wing (BSCW) is a benchmark configuration under eval- uation within the Aeroelastic Prediction Workshops (AePWs). This wing was tested in the NASA Transonic Dynamics Tunnel (TDT) as part of the Benchmark Models Program (BMP) in the 1990s and is expected to be tested again in the TDT in 2025. The data acquired during the BMP tests includes unsteady pressure data and aeroelastic responses at various Mach numbers, dynamic pressures, and angles of attack. At the higher angles of attack, the existence of significant unsteadiness and separated flow results in a challenging case for CFD-based aeroelastic predictions. The AePW workshops have focused on various parts of these BSCW test data and a recent major focus regards the higher angle-of-attack conditions. The NASA AEROM software is applied to this configuration at M=0.8 and several angles of attack to evaluate the capability of the method to capture nonlinear un- steady aerodynamic effects at the higher angles of attack. The AEROM software is applied via the CREATE-AV KESTREL CFD code and AEROM results are compared with results from the CREATE-AV KESTREL solutions. |
| 7.12 We, 17.6. 16:45 - 18:45 | Steady/Unsteady Aerodynamics 3 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 16:45 | 17:15 | 0061 |
Assessment of Linearised Frequency Domain Capability with Overset Meshing D Nash, University of Liverpool, GB The increasing geometric complexity of aircraft designs creates new challenges for computational modelling techniques. There is a need for accurate, and cost effective, predictions of unsteady aerodynamics. To enable this, an assessment of linearised frequency domain capability with overset meshing is presented, demonstrating accuracy over a range of increasingly complex test cases. | |
| 17:15 | 17:45 | 0130 |
Initialisation strategies for aerodynamic instabilities using time spectral method in a new generation flow solver VM Mohan, School of Engineering, University of Liverpool, GB This work investigates initialisation strategies for simulating aerodynamic instabilities using the time spectral method. Three approaches are scrutinised: conventional nonlinear forcing and superposition of the steady state with either an unstable eigenmode or a linear frequency-domain response. We apply the methods to limit-cycle oscillations resulting from vortex shedding and shock buffet. | |
| 17:45 | 18:15 | 0057 |
Linearised frequency domain simulations of folding wingtips with overset meshing S. M. Edwards, University of Liverpool, GB Folding wingtips allow for increased wingspan in flight, improving lift-to-drag ratios. For modelling, computational meshes must be readily deformed to significant fold angles. Traditional deformation methods lead to significant mesh distortions. Here, an overset mesh technique is merged with a linearised frequency domain implementation, for the first time, to calculate aerodynamic loads. | |
| 18:15 | 18:45 | 0320 |
Assessment of Unsteady CFD for Flutter Analysis of Twin-Engine Commercial Airplanes A. Scalabrin, Boeing, US While unsteady CFD methods have long been applied to flutter analysis, its use in industrial settings is still challenging and limited, due to the size and complexity of such aeroelastic models. In this work, a linearized frequency-domain method based on URANS CFD is applied to an industrial case. The challenges and comparison with traditional methods of flutter analysis are discussed. |
| 7.13 We, 17.6. 16:45 - 18:45 | Computational Aeroelasticity 6 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 16:45 | 17:15 | 0039 |
Low Fidelity Model for Hypersonic Aeroelasticity with Shock Impingement and Thermo-Mechanical Buckling D.D. Dooner, UNSW Canberra, AU A low-fidelity model to assist with the design and component analysis of aerothermoelastic panels undergoing buckling and shock impingement. Novel treatments for time-varying material properties are included. The value is internal to in-house experiments, and more broadly to support the work of AePW High-Speed Working Group. | |
| 17:15 | 17:45 | 0052 |
Aerothermoelastic response analysis of hypersonic vehicles based on a CFD-modified engineering method L. Ma, Z.-Q. Wan, X.-Z. Wang; Beihang University, CN We establish a component-level analysis method for aerothermoelastic (ATE) response leveraging full-vehicle-scale data in this paper. Time-domain simulations along the flight trajectory are conducted. The results demonstrate asynchronous characteristics of force loading and thermal loading during flight, giving rise to a distinct ATE response that warrants the attention of researchers. | |
| 17:45 | 18:15 | 0095 |
AERO-THERMAL-ELASTIC ANALYSIS OF A PANEL IN SUPERSONIC FLOW WITH COUPLED NONUNIFORM HEAT TRANSFER NTK Touati Kreimer, Technion, IL This work advances computational aero-thermal-elasticity by analyzing the RC-19 panel flutter tests in a more comprehensive way than considered in prior studies. The thermal problem is formulated as a coupled FEM system for the thin panel and the closed acoustic cavity. We simulate the thermal transient to capture hysteretic buckling and flutter often missed by simplified methods. | |
| 18:15 | 18:45 | 0067 |
FLUID-THERMAL-STRUCTURAL INTERACTION ANALYSIS OF COMPLIANT PANELS UNDER HYPERSONIC FLOW WITH EXPERIMENTAL CORRELATION M. Vieira Cabral, Massachusetts Institute of Technology , US This work is motivated by the fluid–thermal–structural interaction experiments conducted at the AFRL Mach 6 High Reynolds Number Facility (M6HRF). The purpose is to bridge the gap between experimental observations and computational modeling by first considering a case in which thermal loads dominate the aerothermoelastic response, and subsequently incorporating aerodynamic unsteadiness to capture the behavior observed in the later experiments. |
| 7.14 We, 17.6. 16:45 - 18:45 | Aeroservoelasticity 4 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 16:45 | 17:15 | 0190 |
Actuator-induced nonlinear dynamics in gust load alleviation and active flutter suppression L. Marino, TU Delft, NL Actuator rate and acceleration limits fundamentally alter the closed-loop dynamics of load alleviation and flutter suppression systems. Exact analytical methods are developed to assess limit cycle oscillations, global stability and convergence in response to transient perturbations. An experimental investigation is carried out to validate the predicted nonlinear phenomena. | |
| 17:15 | 17:45 | 0293 |
SLENDER BODY WITH TIME-VARYING MASS ELASTIC RESPONSE ESTIMATION USING A KALMAN STATE ESTIMATOR APPROACH I. Genkin, Technion - Israel Institute of Technology, IL This study presents a novel methodology to estimate the in-flight dynamic aeroelastic response of a slender flexible structure with time-varying mass using a Kalman state estimation approach. The removal of the estimated response from the IMU data circumvents the need to filter the data with broad stop-band filters as in conventional methods, thus, acting as an adaptive filter. | |
| 17:45 | 18:15 | 0133 |
Analysis of Limit Cycle Oscillations in Nonlinear Fin-Actuator Systems by Numerical Continuation Z. Liu, Beihang University, CN The characteristics of LCOs in a fin-actuator system with freeplay nonlinearity are acquired by time-domain numerical continuation. A computational scheme is established to enable the direct application of numerical continuation to the block diagram model of the system established in graphical simulation platforms such as Simulink, thereby enhancing the practicality of numerical continuation. | |
| 18:15 | 18:45 | 0234 |
Nonlinear controllability of very flexible aircraft: analysis and implementation L. Zolli, ISAE-SUPAERO, FR The paper introduces a new algorithm for tracking LED markers on a flexible wing with a single camera, based on image processing and Kalman filtering, used as a component of an onboard wing shape estimation system. Its precision, bandwidth (exceeding previous results by 50%) and robustness to environmental conditions are demonstrated experimentally on a static testbench. |
| 7.15 We, 17.6. 16:45 - 18:45 | General Topics in Aeroelasticity Chair: N.N. | ALTE MENSA - Room Taberna |
| 16:45 | 17:15 | 0069 |
Aeroelastic Modelling and Analysis of Curved Composite Propeller Blades P. M. van Veen, TU Delft, NL An aeroelastic analysis tool for composite propeller blades with sweep and lean is developed, based on a low-fidelity aerodynamic model tightly coupled to a structural model. This tool is used to study the effect of sweep and lean on the aerodynamic performance and structural response of composite propeller blades, showing that blade curvature affects both aerodynamic efficiency and blade stress. | |
| 17:15 | 17:45 | 0093 |
THREE-DIMENSIONAL LARGE DEFORMATION RECONSTRUCTION OF WIND TURBINE BLADES BASED ON STRAIN MEASUREMENT C.-C. Xie, M.-Z. Zheng, Y. Meng; Beihang University, CN With the continuous increase in wind turbine capacity and blade size, wind turbine blades exhibit increasingly pronounced flexible responses under complex aerodynamic loading conditions. In recent years, several catastrophic accidents, including blade fracture and collapse events, have demonstrated that conventional deformation monitoring techniques—typically relying on sparse displacement measurements or linear assumptions—are no longer sufficient to meet the accuracy requirements of high-fidelity structural health monitoring. To address this challenge, this paper proposes a three-dimensional large-deformation reconstruction method for wind turbine blades based on strain measurement technology. To overcome the constraints on sensor placement on blade surfaces, a sensor layout optimization method is developed by jointly considering reconstruction error and spatial distribution constraints. An improved genetic algorithm is employed to optimize sensor locations over the entire blade. By dynamically adjusting the crossover and mutation probabilities, the algorithm maintains a high crossover probability and low mutation probability at higher fitness levels, and a low crossover probability and high mutation probability at lower fitness levels, thereby achieving a better balance between global exploration and local convergence. The incorporation of elitist preservation and tournament selection strategies further enhances the convergence efficiency and robustness of the algorithm. For deformation reconstruction, the blade geometry is mathematically represented using a central reference line and a series of beam-like cross sections, and a modal rotation method[1] is adopted to reconstruct the deformed configuration. Unlike conventional approaches based on modal displacements, the modal rotation method computes the spatial position of the reference line using modal rotation angles, enabling more effective treatment of geometric nonlinearities in complex structures. | |
| 17:45 | 18:15 | 0219 |
A COMPUTATIONALLY EFFICIENT AEROELASTIC MODEL OF WIND TURBINE BLADES INTEGRATED WITH A LATTICE BOLTZMANN METHOD SOLVER G.S.R. de Sá, ITA (Instituto Tecnológico de Aeronáutica), BR A computationally efficient structural solver for wind turbine blades is developed for two-way coupling with high-fidelity LBM-LES aeroelastic frameworks. By retaining the dominant blade dynamics with a minimal number of degrees of freedom, the approach enables accurate time-domain simulations without introducing a structural computational bottleneck. | |
| 18:15 | 18:45 | 0140 |
Dynamic characteristics of an external aircraft panel with a tailored damping treatment S. D. Jayatilake, University of Bristol, GB External lightweight panels in aircraft are prone to a range of detrimental aerodynamic excitations and aeroelastic instabilities. This paper investigates the dynamic stability of a sandwich panel with a non-uniformly distributed, sandwiched viscoelastic treatment. The aim is to identify secondary impacts of highly optimised damping treatments on the dynamic stability of panel structures. |
| We, 17.6. 18:45 - 18:46 | End of IFASD 2026 | Day 2 | 18:45 - 18:46 | ||||||
| We, 17.6. 19:30 - 23:30 | Networking Evening @ BULLERJAHN | 19:30 - 23:30 | ||||||
| Th, 18.6. 08:00 - 08:30 | Registration opens | 08:00 - 08:30 | ||||||
| 0.3 Th, 18.6. 08:30 - 09:15 | Plenary 3 Chair: L. Tichy, German Aerospace Center, DE | |||
| 08:30 | 09:15 |
TBD Pascal Lubrina, ONERA | ||
| Th, 18.6. 09:15 - 09:30 | Room Change | 09:15 - 09:30 | ||||||
| 8.11 Th, 18.6. 09:30 - 11:00 | Aeroelasticity in Conceptual Aircraft Design 6: Folding Wingtips Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 09:30 | 10:00 | 0178 |
Extended stability and stability boundary reduction analysis of flexible aircraft with folding wingtips L. Dehmlow, TU Berlin, DE Flared folding wingtips (FWT) enable higher aspect ratio wings and passive load alleviation while meeting airport gate limits. The interaction between FWT dynamics, aircraft flexibility and flight dynamics while considering geometric nonlinearities have not been studied yet. The objective is to analyse the influence of different aircraft and FWT parameters on the stability and flight dynamics. | |
| 10:00 | 10:30 | 0160 |
AEROELASTIC ANALYSIS OF RAKED FOLDING WINGTIPS ON SWEPT WINGS F Sacchi, University of Bristol, GB Flared Folding Wingtips (FFWTs) are a solution for reducing in-flight loads, but are limited by the occurrence of flutter. Initial results for a reduced sized model, 1.34m wingspan, AR 17 and a 0.34m span FFWT with 10deg flare angle, have shown that for a 10deg forward swept wing, the flutter speed can be increased by up to 37% when using FFWT rake without any weight penalties. | |
| 10:30 | 11:00 | 0252 |
A COMPUTATIONAL FRAMEWORK FOR ANALYZING FOLDING WING TIP DYNAMICS ON HIGHLY FLEXIBLE WINGS: A FLEXIBLE MULTIBODY FORMULA L. Barros da Luz, Instituto Tecnológico de Aeronáutica, BR A flexible multibody aeroelastic framework is presented for highly flexible wings with passive folding wing tips, combining Rayleigh–Ritz structural modeling and non-planar VLM with a deforming aerodynamic mesh. Validated against structural and aeroelastic benchmarks, the tool predicts substantial gust load alleviation, with up to 24.3% reduction in wing-root bending. |
| 8.12 Th, 18.6. 09:30 - 11:00 | Dynamic loads 1: Buffet Loads Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 09:30 | 10:00 | 0134 |
AERO-STRUCTURAL MODELING AND PREDICTION OF TRANSONIC SHOCK-BUFFET LOADS ON AN F-16 WING T. Nahom Jidovetski, Technion – Israel Institute of Technology, IL A coupled aero-structural framework is developed to predict buffet-induced wing loads on an F-16 using unsteady pressure measurements. Reconstructed time-domain aerodynamic forces are coupled with a structural dynamic model to quantify buffet contributions and assess the influence of external-store configurations. The approach is validated against wind-tunnel and flight-test data. | |
| 10:00 | 10:30 | 0071 |
COMPARATIVE STUDY OF BUFFET RESPONSE IN SINGLE-FIN AND TWIN-FIN COMBAT AIRCRAFT U PV, AERONAUTICAL DEVELOPMENT AGENCY, IN Modern fighter aircrafts are designed for high agility and are required to perform manoeuvres at high angles of attack (AOA). The aircraft encounters highly adverse aerodynamic conditions, characterized by the formation of strong vertical flows originating from forward surfaces, including the forebody, air intake and wings. As the angle of attack increases, these vortices may become unstable and undergo breakdown. The resulting unsteady flow impinges on the vertical and horizontal tail surfaces, producing fluctuating pressure loads that can excite their structural modes. The induced dynamic response can be significant, leading to possible structural damage and a substantial reduction in the fatigue life of critical aircraft components. The buffet mechanism is strongly influenced by aircraft configuration, particularly the position and orientation of the vertical tails. In single-fin configurations, the vertical tail is aligned with the fuselage reference line (FRL), whereas twin-fin configurations employ outward-canted vertical tails, making them more susceptible to tail buffeting, especially at high AOA This paper presents a comparative study of buffet characteristics in fourth-generation single-fin combat aircraft and a fifth-generation advanced medium twin-fin combat aircraft based on wind tunnel experiments. The comparison study focuses on unsteady pressure distribution, aeroelastic buffet response, buffet onset, and buffet severity for both configurations under identical test conditions. Wind tunnel tests were conducted in subsonic and transonic regimes over a range of Mach numbers, angles of attack, and angles of sideslip. The single-fin aircraft was tested using a 1:20 scaled model in the 4-ft Transonic Wind Tunnel at the National Aerospace Laboratories (NAL), India. The model comprises a vertical tail and delta wings equipped with ailerons, flaperons, and slats. The twin-fin aircraft was tested using a 1:15 scaled model in the 8-ft Transoni | |
| 10:30 | 11:00 | 0261 |
Buffet Loads Recovery from PSD Least Square Regression of Inflight Accelerations and Airframe Digital Twin D. Monti, Leonardo Aircraft Division, IT Buffet Loads are often dimensioning loads. Unfortunately their simulation is difficult because it depends on unsteadiness in aerodynamics. We believe that an hybrid approach based on inflight accelerations and airframe digital twin can achieve the desired results, even not knowing the aerodynamic unsteadiness. Our approach is based on a regression of analytical PSD matching inflight measurements in frequency domain. |
| 8.13 Th, 18.6. 09:30 - 11:00 | Computational Aeroelasticity 7 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 09:30 | 10:00 | 0081 |
Quantification of Non-linear Aerodynamic Effects on the Limiting Gust Load Cases K. M. Streitenberger, German Aerospace Center, DE Different types of transonic non-linear effects during gust encounter can influence the dynamic loads acting on the wing. In this talk, time domain computational fluid dynamics will be used to quantify the impact of these non-linear effects on the limiting gust load cases and classify different regions inside the flight envelope. The results of the non-linear simulation will be also compared to a linear reference. | |
| 10:00 | 10:30 | 0050 |
DLM- AND CFD-BASED CONTINUOUS TURBULENCE ENCOUNTER FOR A HIGH ASPECT RATIO CONFIGURATION D. Friedewald, DLR, DE Load collectives and aerodynamic coefficients obtained from the DLM-based and CFD-based simulations will be compared for a high aspect ratio configuration in continuous turbulence encounters, providing insight into how the higher-fidelity CFD modelling influences the aircraft’s load spectrum relative to the conventional DLM. | |
| 10:30 | 11:00 | 0249 |
HIGH-FIDELITY AEROELASTIC ANALYSIS OF PASSIVE FOLDING-WING CONCEPTS FOR GUST LOAD ALLEVIATION: COUPLED CFD/CSD STUDY M. Ahmadi, adana science and technology university, TR We present a coupled ANSYS Fluent-Mechanical FSI framework to design and assess a passive folding wingtip on an optimized high-aspect-ratio composite wing. Simulations under 1-cosine and harmonic gusts show reduced wing-root bending moments, demonstrating a low-complexity morphing route to improve aeroelastic loads and ride comfort without weight or control penalties. |
| 8.14 Th, 18.6. 09:30 - 11:00 | Aeroservoelasticity 5 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 09:30 | 10:00 | 0112 |
AEROSERVOELASTIC MODEL IN TIME DOMAIN AND A NOVEL APPROACH TO COUPLE THE FLIGHT MECHANICS-AEROSERVOELASTICITY LUCA DI SIVO, EDOARDO ORAZI, STEFANO RAIMONDO; LEONARDO SpA, IT Presented by: Di Sivo, LEONARDO AERONAUTICS – AIRCRAFT BU A novel approach, that couples the Aeroelasticity and the Flight Mechanics (FM) state-space models, that includes inertial and aerodynamic coupling terms between elasitc-rigid modes. Elastic-rigid mutual effects are introduced as additional forces/moments into the state-space of the FM at each time step simulating the correct rigid behaviour of the flexible A/C. Non linearities may be investigated | |
| 10:00 | 10:30 | 0300 |
A Control-Oriented Aeroelastic Modelling Framework for Compliant Wings with Trailing-Edge Morphing A. Balon, CTU in Prague, FME, CZ A lightweight aeroelastic modelling framework for trailing-edge morphing wings is presented, enabling the efficient generation of control-oriented models that retain the essential physics of morphing wing behaviour. The approach supports rapid simulation and reduced-order modelling for the design of multi-objective controllers that exploit the advantages of spanwise trailing-edge morphing. | |
| 10:30 | 11:00 | 0279 |
Updated Aeroservoelastic Model of an Active Flutter Suppression Demonstrator Aircraft T. M- Kier, DLR, DE An AFS system was successfully tested in flight. However, the AFS control laws were designed based on an old status of the FEM model. An aeroservoelastic model is presented updated with GVT results, a DLM model capturing the in-plane forces and a new actuator tf, matching the flutter speed and damping of the flight test data. Performance and robustness of the AFS are assessed in a SIL simulation. |
| 8.15 Th, 18.6. 09:30 - 11:00 | Rotorcraft Aeroelasticity 3 Chair: N.N. | ALTE MENSA - Room Taberna |
| 09:30 | 10:00 | 0142 |
AN INTEGRATED FRAMEWORK FOR AEROELASTIC RESPONSE ANALYSIS OF PROPELLER-WING SYSTEMS N.-R. Niu, Beihang University, CN This article develops an integrated and robust time-domain simulation framework that utilizes the Unsteady Vortex Lattice Method (UVLM) coupled with structural dynamics models. This framework captures the unsteady aerodynamic interferences between the propeller and the wing while accounting for the follower force effects of the propeller. This research provides a comprehensive analysis of the aeroelastic behavior of a propeller-wing configuration and identifies the key mechanisms of the system's aeroelastic response. These insights provide critical engineering guidance for the design of next-generation propeller aircraft, emphasizing the necessity of detailed aeroelastic analysis for these systems. | |
| 10:00 | 10:30 | 0187 |
TOWARDS ROBUST WHIRL FLUTTER PREDICTION IN PROPELLER AIRCRAFT: A CRITICAL REVIEW OF MODELING PARAMETERS C. Koch, German Aerospace Center (DLR), DE This paper condenses the individual findings of previous studies on the effect of blade aerodynamic modelling, blade elasticity, propeller operating point and aerodynamic interaction on the whirl flutter stability of turboprop aircraft. It discusses the impact of modeling choices on the accuracy of flutter predictions as well as on computational cost. | |
| 10:30 | 11:00 | 0179 |
Effect of swirl recovery vanes on propeller whirl flutter V. Marletta, German Aerospace Center (DLR), DE This paper explores the effect of swirl recovery vanes (SRVs), e.g., used in Open-Fan engines, on unsteady propeller loads and whirl flutter. It shows that the SRVs mainly contribute to the inplane forces and only a bit to the inplane moments. The presence of SRVs only has a minor effect on the whirl flutter stability of a simplified 2-DOF whirl flutter system. |
| Coffee Break | 11:00 - 11:30 | |||||||
| 9.11 Th, 18.6. 11:30 - 13:00 | Aeroelasticity in Conceptual Aircraft Design 7: Distributed Propulsion Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 11:30 | 12:00 | 0256 |
NUMERICAL VALIDATION OF A HIGH-ASPECT RATIO WING FLEXIBLE AIRCRAFT MODELLED IN AN ENHANCED LOW-FIDELITY FRAMEWORK W. Mickein, TU Berlin, DE This work describes the methodology behind the ModSiG framework, with a particular focus on the novel approximation implemented to include quasi-steady transonic corrections. The derived model is numerically validated for the DLR-F25 virtual reference aircraft through a comparative analysis of its longitudinal behaviour against full CFD data in the time- and frequency-domains. | |
| 12:00 | 12:30 | 0296 |
AEROELASTIC OPTIMIZATION OF FLEXIBLE AIRCRAFT WINGS WITH DISTRIBUTED ELECTRIC PROPELLERS S.-T. Dede, University of Bristol, GB This study investigates minimizing structural wing weight in DEP aircraft by optimizing wing box thickness within the design constraints using Genetic Algorithms. It introduces a novel integration of efficient aeroelastic models and optimization methods to design flexible, multi rotor wings while accounting for flutter constraints. | |
| 12:30 | 13:00 | 0034 |
Aeroelastic Shape Optimization of a Hybrid Regional Aircraft with Distributed Propulsion R Maierl, Airbus Defence and Space, DE At Airbus in Manching the foundation is the structural optimization software Lagrange which has been developed in our perimeter for over 40 years. Recent developments were undertaken to provide model based structural sizing optimization during the concept phase via surrogate models. This approach is suited to front-load the calculation effort of design studies with large numerical models and to include models which don’t return design sensitivities |
| 9.12 Th, 18.6. 11:30 - 13:00 | Dynamic loads 2: Gust Loads Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 11:30 | 12:00 | 0121 |
Differentiable Gust and Maneuver Loads at Scale on Very Flexible Aircraft R. Palacios, Imperial College London, GB A method for large-scale computation of static and dynamic aeroelastic loads is discussed. It is built on a geometrically nonlinear simulation framework with concurrent capabilities that has be deployed on modern hardware architectures. It construct load envelopes for static and dynamic cases in seconds without using surrogates for industrial-scale aircraft models. Differentiation of both concurrent computations and aeroelastic loads is achieved via JAX library automatic differentiation engine and collective primitives. Discrete, maneuver and gust loads are assessed for multiple flow and parametric conditions running concurrently. Sensitivities of maximum wing-root stresses and tip displacements are computed and verified against finite differences. | |
| 12:00 | 12:30 | 0229 |
HEAVY TURBOPROP AIRCRAFT IN FIREFIGHTER CONFIGURATION. GUST LOADS ALLEVIATION FUNCTION EFFECTIVENESS AND 1P LOADS MODEL R Navarro Romero, AIRBUS OPERATIONS, ES The present paper introduces a couple of details found during a Heavy Transport Turboprop Aircraft (HTTA) gust analyses in firefighter configuration. Both are particularly relevant during low-speed operations demanding high manoeuvrability and gust encounter. The first technical aspect is associated to the Gust Loads Alleviation (GLA) function, and the limited effectiveness in reducing the wing root bending moment for these kinds of operations. The second technical detail, is associated to the incremental 1P loads for high induced angles of attack, and the fidelity of simple linear models in the representation of this physical phenomenon. | |
| 12:30 | 13:00 | 0011 |
STATISTICAL DISCRETE GUST METHOD FOR ATMOSPHERIC TURBULENCELOADS IN AEROELASTIC RESPONSE MODELS V.H. Moreira, ITA - Aeronautical Technology Institute, BR Technical innovation:SDG method using solutions in the frequency-domain; previously applied in the time-domain only. The main result:Comparison indicates a meaningful overlap between PSD and SDG methods for gust design-envelope, and exceedance curves from mission-analysis shows the PSD method tends to overestimate loads at large turbulence amplitudes, both in agreement with other authors results. |
| 9.13 Th, 18.6. 11:30 - 13:00 | Computational Aeroelasticity 8 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 11:30 | 12:00 | 0124 |
Aeroelastic stability calculations of a laminar wing using viscous-inviscid interaction A. Crovato, ONERA, FR This work proposes a novel approach for calculating the flutter of laminar wings. A steady flow solution is first calculated by means of a viscous-inviscid interaction methodology, which is then used to correct an unsteady compressible source and doublet panel method. Finally, the flutter solution is calculated using a non-iterative p-k method. The method is demonstrated on the CAST 10 airfoil. | |
| 12:00 | 12:30 | 0286 |
High-fidelity aerodynamic models for propeller-wing whirl flutter F. Iorio, Safran Aircraft Engines, FR In this work, a method to perform whirl flutter stability analysis of a wing-mounted propeller using high-fidelity URANS simulations, integrating blade flexibility, is demonstrated and compared with legacy analytical models. Results show the high-fidelity model validates the analytical ones, also revealing the importance of the including wing aerodynamics. | |
| 12:30 | 13:00 | 0189 |
Flutter analysis of a hose-drogue system with aerodynamic grid fins for aerial refueling K. Salehi Paniagua, Universidad Politécnica de Madrid, ES This work introduces a novel passive stabilization concept for hose–drogue aerial refueling systems based on the integration of aerodynamic grid fins at the hose–drogue junction. A validated aeroelastic model shows that grid fins significantly increase stability margins and shift flutter boundaries to higher speeds, which could improve refueling safety. |
| 9.14 Th, 18.6. 11:30 - 13:00 | Steady/Unsteady Aerodynamics 4 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 11:30 | 12:00 | 0026 |
Control surface modeling: analysis of unsteady effects of spanwise gaps using linearized frequency-domain solvers L.B. Streher, DLR, DE Control surfaces dynamically modify the geometry of an aircraft, altering the surrounding flow field and inducing unsteady aerodynamic loads. Accurately predicting these effects is essential for reliable flight-load assessments. However, incorporating control-surface deployment in high-fidelity computational fluid dynamics (CFD) simulations remains challenging, particularly due to the presence of small geometric gaps. While streamwise gaps are typically sealed, spanwise gaps are not, as closing them would require advanced morphing technologies. These spanwise gaps generate complex circulation patterns and large vortical structures that convect downstream, making their aerodynamic impact non-negligible. This work investigates these effects using NASA’s Benchmark Active Controls Technology (BACT) model, a rectangular wing with a NACA 0012 section equipped with upper and lower spoilers and a trailing-edge control surface. Extensive experimental data exist for harmonically oscillating trailing-edge surfaces, covering variations in frequency, initial position, and amplitude. The sensitivity of in-phase and out-of-phase pressure coefficients to control surface oscillation amplitude and initial position makes this configuration an excellent candidate for assessment with linearized frequency-domain (LFD) solvers. Two numerical configurations are studied: a clean wing and a wing including the spanwise gaps. The clean-wing mesh is easily generated, and control-surface motion is modeled using mesh deformation with a blending approach. In contrast, the gapped configuration requires significantly more complex meshing due to the narrow gaps and the need to generate boundary-layer elements in this constrained region. An overset-grid strategy is employed, with separate grids for the lifting and control surfaces coupled via sliding-interface boundaries. Control-surface motion is obtained through a mesh-deformation algorithm applied exclusively to the control-surface grid, with | |
| 12:00 | 12:30 | 0042 |
High Fidelity CFD Shock wave and Control Surface evaluation G. Claudino e Silva, ITA, BR This research results will allow for a more robust investigation and characterization of the oscillatory motion of the shock wave formation on handling qualities and stability evaluations of transonic flow projects by promoting a comparison between different CFD fidelity configurations on a sample test. | |
| 12:30 | 13:00 | 0018 |
SEMI-AKTIVE FLUTTER SUPRESSION USING CONTROL SURFACE DEFLECTIONS K. Bantscheff, Technische Universität München, DE This work presents a proof of concept for a modified ADHF system that influences the flutter boundary. Insights from the non-oscillating profile are used to project to the actual elastic behavior. To verify this, an additional comparison between the flutter boundary of the clean and the modified profile is conducted, enabling a free two-degree rigid body motion of each profile. |
| 9.15 Th, 18.6. 11:30 - 13:00 | Highly Flexible Aircraft Structures 1 Chair: N.N. | ALTE MENSA - Room Taberna |
| 11:30 | 12:00 | 0274 |
Comparison of Low-order Nonlinear Aeroelastic Models for Numerical Continuation F Healy, University of Bristol, GB This work compares low?order nonlinear structural–aerodynamic models for their suitability in numerical continuation of aeroelastic systems. Using three benchmark wings, it identifies which modelling choices enable robust prediction of Hopf bifurcations and limit?cycle oscillations, supporting future design of experimental and wind?tunnel aeroelastic demonstrators. | |
| 12:00 | 12:30 | 0316 |
NONLINEAR AEROELASTIC BEHAVIOUR OF FLEXIBLE HAPS WINGS AND ITS IMPACT ON LOAD DISTRIBUTION, TRIM AND CONTROL O.Y. Havaza, National Technical University of Ukraine “Igor Sikorsky Kyiv Pol, UA We study nonlinear aeroelastic effects in highly flexible HAPS wings, predicting deformation-driven redistribution of aerodynamic loads and its impact on trim and control effectiveness. Using a symbolic reduced-order framework (IFASD 2024 #235), we enable rapid parametric studies and mass-driven stiffness tailoring to maintain aeroelastic margins. | |
| 12:30 | 13:00 | 0182 |
EXPLOITING CONTROL REVERSAL FOR SIMULTANEOUS ACTIVE AND PASSIVE MANOEUVRE LOAD ALLEVIATION E. Filippou, Delft University of Technology, NL This work shows that deliberately operating control surfaces beyond their reversal point enables simultaneous active and passive load alleviation without sacrificing roll control. Applied to a transport wing, the approach yields a 13.3% structural mass reduction. The results challenge conventional design limits and offer a new path to lighter, more efficient aeroelastic aircraft structures. |
| Networking Lunch & Poster Session | 13:00 - 14:15 | |||||||
| 10.11 Th, 18.6. 14:15 - 15:45 | Aeroelasticity in Conceptual Aircraft Design 8: Methods and Frameworks Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 14:15 | 14:45 | 0056 |
Inertial Relief in Fluid Structure Interaction Problems with Analytic Sensitivities D. Clemens, University of Dayton Research Institute, US Inertial relief is a technique by which to analyze free-flying bodies like aircraft, but analysis methods require analytic sensitivity support for use in robust design optimization. This work details how inertial relief with sensitivity analysis was incorporated into an AFRL FEA solver, integrated into aeroelastic design optimization routines, and demonstrated on a generic flying wing model. | |
| 14:45 | 15:15 | 0070 |
Validation of a Nonlinear Vortex-Lattice Method Framework for Static Aeroelastic Analyses of a Full Aircraft L. Adams, École Polytechnique Montréal, CA For aircraft aeroelastic analyses, recent adaptations of the Vortex-Lattice Method have shown interesting results with potential to replace the industry standard Doublet-Lattice Method. This work explores the impact of aerodynamic models (VLM, nonlinear VLM, DLM and RANS) on static aeroelastic analyses for a full aircraft configuration. Analyses are performed for control reversal. | |
| 15:15 | 15:45 | 0263 |
Prediction of Geometric Nonlinear Steady Flight Loads via extended Modal Rotation Method J Grigoleit-Hilger, DLR - German Aerospace Center, DE A novel approach for the prediction of geometric nonlinear steady flight loads will be presented. Therefore, the Modal Rotation Method (MRM) is implemented and adapted and coupled with a geometrically nonlinear vlm implementation. The developed framework is used for steady flight load predictions of the TUFlex aircraft, showing the differences between nonlinear and linear analyses. |
| 10.12 Th, 18.6. 14:15 - 15:45 | Dynamic loads 3: Special Loads Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 14:15 | 14:45 | 0077 |
INFLUENCE OF LANDING GEAR SHOCK ABSORBER DAMPING ON AIRFRAME LOADS AND ACCELERATIONS D. Fleischer, AIRBUS Defence and Space, DE Ground loads form a fundamental input for A/C design. In this work the focus is on ground loads generated by A/C landing impacts for a UAV. With a given Multi-Body Simulation model based on a flexible model of LG and airframe, loads and accelerations are assessed. Furthermore, the setting of the main landing gear shock absorber damping is varied in order to reduce loading on airframe level. | |
| 14:45 | 15:15 | 0119 |
DYNAMIC RESPONSE ANALYSIS OF PYLON RELEASE FOR FLEXIBLE AIRCRAFTS C. Song, Beihang University, CN Establishes flexible aircraft flight dynamics equations under mean axis coordinates, and develops a small-disturbance state-space model accounting for mass change and ejection impact during pylon release. Overcomes inaccuracies of rigid-body models and inefficiency of mainstream CFD-CSD coupling. Reveals structural flexibility’s non-negligible effect on transient responses. | |
| 15:15 | 15:45 | 0017 |
Modeling and Analysis of Structural Loads of a Flexible Transonic Aircraft using Strip-Theory Flight Dynamics L.-H. Lemke, Hamburg University of Technology, DE Structural load alleviation is a key technology to enable very efficient high aspect ratio wings on commercial aircraft. In this paper, requirements are developed to contextualize alleviation gains with respect to system efforts and certification limits. Therefore, a strip-theory based flight dynamics model of a flexible aircraft including 3D transonic aeroelastic effects is presented and used. |
| 10.13 Th, 18.6. 14:15 - 15:45 | Computational Aeroelasticity 9 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 14:15 | 14:45 | 0108 |
DESIGN-ORIENTED STRESS-BASED HIGH FIDELITY AEROELASTIC GUST CONSTRAINTS B.K. Stanford, NASA LaRC, US This work considers the analysis and gradient computation of dynamic stresses due to discrete gusts, for an aeroelastic transport configuration. Unsteady aerodynamics are computed with high-fidelity CFD, and dynamic stresses are computed with modal acceleration. | |
| 14:45 | 15:15 | 0177 |
Gust Load Alleviation (GLA) Controller Synthesis Using High-Fidelity Transonic Aerodynamics DMR Matas Ruiz, DLR (German Aerospace Center), Institute of Aeroelasticity, DE Synthesis of a Gust Load Alleviation controller for a NACA64A010 airfoil using high-fidelity transonic aerodynamic models from DLR's TAU CFD and FSFM LFD solvers at three angles of attack. Tangential interpolation via the Loewner framework enabled a reduced-order, time-continuous model. The H-infinity controller accounts for the influence of the steady-state angle of attack. | |
| 15:15 | 15:45 | 0040 |
Aeroel. Damping Augmentation and Flutter Analysis for a High-Aspect-Ratio Wing Aircraft in the Transonic Flight Regime M. Fehrs, DLR, DE This paper demonstrates a workflow for the design and verification of Active Flutter Suppression controllers in transonic flow. The investigation is part of the DLR project ACTIVATE, which main goal is to develop an understanding of active and semi-active approaches for flutter suppression at transonic Mach numbers. The workflow is demonstrated for a high aspect ratio wing aircraft configuration. |
| 10.14 Th, 18.6. 14:15 - 15:45 | Active Control and Adaptive Structures 3 Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 14:15 | 14:45 | 0225 |
Multidimensional Loads Criteria for Active Load Alleviation Control Design C. Wallace, DLR (German Aerospace Center), DE Active control is providing the opportunity to alleviate structural loads, to resize the aircraft primary structure and to save weight. The use of multidimensional load envelopes as part of the control design criteria is not common, therefore a new approach allowing the high-level specification of multidimensional load envelope targets as one of several control design criteria is presented. | |
| 14:45 | 15:15 | 0169 |
Design of a Decentralized Gust Load Alleviation Control Law with a Primary Flight Controller in the Loop J. Martins, DLR - German Aerospace Center, DE This will extend previous works by redeveloping the control design of a decentralized GLA controller and introducing a primary flight controller in the loop. The focus is on the interaction between the flexible and rigid-body modes. It will show the potential of the approach at enabling any aircraft with GLA properties alongside a primary flight controller with minimal work and integration steps. | |
| 15:15 | 15:45 | 0035 |
The Effect Of Wingbox Elastic Deformation On The Morphing Shapes Of The Translation Induced Camber Concept I.T. Tsatsas, TU Delft, NL Until now the morphing concepts have been tested either in wind tunnel or on bench tests using rigid wingboxes to attach the morphing surfaces ignoring the carrying wingbox deformation. This work examines for the first time the effect of the wingbox elastic deformation on the morphing shapes and the actuation force requirements of the Translation Induced Camber morphing concept. *I would like to participate in IFASD Student Best Paper Award |
| 10.15 Th, 18.6. 14:15 - 15:45 | Highly Flexible Aircraft Structures 2 Chair: N.N. | ALTE MENSA - Room Taberna |
| 14:15 | 14:45 | 0242 |
Aerostructural Analysis and Optimization using Viscous-Inviscid Interaction P. Dechamps, University of Liège, BE The use of a Viscous-Inviscid Interaction methodology to perform aeroelastic analysis and optimization of wings in transonic flows is explored. A novel analytical adjoint methodology is presented to compute the required gradients used to drive the optimization. The methodology is compared to a reference static aeroelastic benchmark and the optimization of the Simple Transonic Wing. | |
| 14:45 | 15:15 | 0047 |
A Generalized Condensation Method for Field-Based Structures H. Smith, Air Force Research Laboratory, US Density-based topology optimization cannot directly model major load paths as a subset of the model's nodes due to the underlying field-based representation. Herein we introduce a general condensation strategy to obtain structural beam models from a density-based representation, thereby enabling condensation methods to efficiently model nonlinear structural dynamics for topology optimization. | |
| 15:15 | 15:45 | 0048 |
Skin-buckling induced passive load alleviation D. Hahn, TU Braunschweig, Institut für Flugzeugbau und Leichtbau, DE This research investigates a concept of passive load alleviation based on tailored skin buckling, which nonlinearly increases the bend-twist-coupling of the outer wing to reduce local lift. Reducing loads reduces weight. The concept is evaluated in high fidelity simulations including fluid structure interaction for the first time, resulting in bending moment reductions of approximately 10%. |
| Coffee Break | 15:45 - 16:15 | |||||||
| 11.11 Th, 18.6. 16:15 - 17:45 | Aeroelasticity in Conceptual Aircraft Design 9: Opt. (2) Chair: N.N. | ASSEMBLY HALL - Auditorium |
| 16:15 | 16:45 | 0064 |
NASA Langley Contributions to the Aeroelastic Optimization Benchmark Working Group A Thelen, NASA Langley Research Center, US SciTech 2024 marked the beginning of the High-Fidelity Aeroelastic Optimization Benchmark Working Group, which seeks to compare analysis and optimization results. Having tackled the first problem, which seeks to minimize wing structural mass via structural sizing, this IFASD submission will extend our tools to benchmark cases that instead minimize fuel burn with shape design variables included. | |
| 16:45 | 17:15 | 0143 |
Aerostructural optimization of a business jet wing L. Jousseaume, Dassault Aviation, FR This paper describes the industrial process developed at Dassault Aviation to automatically generate parametric meshes including mass modeling, which aims to quickly compute an optimized mass response surface in the preliminary design phase in order to help the designers find the optimal wing planform. | |
| 17:15 | 17:45 | 0262 |
THE DLR-D2AE â A SHORT MEDIUM RANGE AIRCRAFT CONFIGURATION FOR AEROEALSTIC INVESTIGATIONS T. Klimmek, DLR, Institute of Aeroelasticity, DE The DLR-D2AE, featuring a high aspect ratio wing and wing-mounted landing gear, is a viable design for next-generation aircraft. Its parameterized model setup allows extensive parameter variation. By utilizing simulation models for structure, mass, and aerodynamics, researchers can efficiently examine various aspects of this advanced configuration. |
| 11.12 Th, 18.6. 16:15 - 17:45 | Computational Aeroelasticity 10 Chair: N.N. | ALTE MENSA - v.Trott Hall |
| 16:15 | 16:45 | 0096 |
Framework for Efficient and Robust Prediction of Freeplay Induced Limit Cycle Oscillations with Consideration of Preload V. Motta, Airbus Defence and Space GmbH, DE A framework embedding tools and best practices are developed, to close the capability gap of standard work for limit cycle oscillation (LCO) assessments, to design and service support purposes. LCOs from geometrical nonlinearities i.e. from freeplay caused by wear in mechanical supports/actuation chain, are primarily targeted. The modularity of the tools enables to embed high fidelity aerodynamics and further nonlinearity sources, e.g. from aerodynamics or structure. Frequency domain strategies and targeted numerical methods to predict onset, amplitude, and frequency of LCOs and chaotic regimes have been assessed. Analytical formulations and numerical schemes have been being developed, verified and validated for a 2D three degree of freedom typical section aeroelastic model. These methods will be extended to isolated wings and to full aircraft models, including controller dynamics. Design stages, aircraft configurations, and flight points critical to LCO assessments will be also identified, and included into the design practices. | |
| 16:45 | 17:15 | 0055 |
AERODYNAMIC DAMPING DURING CLASSIC SURGE C. Reiber, DLR, DE This study uses an improved, physically comprehensive method for predicting flutter stability with high time resolution across all compressor surge phases. Unlike previous analyses largely restricted to reversed flow, the results show that flow breakdown and regeneration can lead to negative aerodynamic damping and must therefore be considered for reliable flutter prediction. | |
| 17:15 | 17:45 | 0227 |
DATA-DRIVEN AEROACOUSTOELASTIC ASSESSMENT OF LAUNCHER PAYLOADS R. Giansante, University of Tuscia, IT This study models the internal noise in a launcher fairing using a one-way vibroacoustic approach. Fairing vibrations, forced by external unsteady pressure predicted via machine-learning, generate the internal acoustic field. The analysis evaluates the acoustic spectrum for three structural configurations and includes a parametric study of wall impedance. |
| 11.13 Th, 18.6. 16:15 - 17:45 | Computational Aeroelasticity 11 Chair: N.N. | ALTE MENSA - H.Vogt Hall |
| 16:15 | 16:45 | 0218 |
AERO-SERVO-ELASTIC ANALYSIS OF 2D AIRFOIL IN ALLEVIATING TRANSONIC FLOW-INDUCED VIBRATIONS THROUGH FLAP CONTROL H.C. Önel, Adana Science and Technology University, TR Transonic instabilities in flexible wings exceed linear theory due to shock dynamics. This study uses a high-fidelity OpenFOAM-preCICE framework to evaluate active flap control. A PID controller successfully stabilizes vibrations, converging to a 14 deg deflection. The work provides a robust platform for validating control laws in nonlinear regimes. | |
| 16:45 | 17:15 | 0310 |
On the modelling and simulation of body-freedom aeroelasticity of morphing air-launched UAVs S.J. van Elsloo, Faculty of Aerospace Engineering, TU Delft, NL In this work, we study the characteristics of the flight dynamics and structural dynamics of air-launched UASs during the launch phase. This has been achieved by developing a custom UVLM-VPM model, and coupling it through a custom co-simulation framework with flight dynamic and structural dynamic models. The model has been applied to a Goland wing and a sweep-morphing UAS during its launch. | |
| 17:15 | 17:45 | 0306 |
A Method for the Geometrically Nonlinear Computation of Maneuver Loads in Preliminary Design of Jet Transports M. R. Ritter, DLR, DE In this work we present an approach for the computation of quasi-steady maneuver loads in preliminary design which considers geometric nonlinearities caused by large deformations. The method is based on the extended modal approach and uses a condensed structural model. Aerodynamic forces are calculated by CFD, therefore both aerodynamic and structural nonlinearities are taken into account. |
| 11.14 Th, 18.6. 16:15 - 17:45 | Flight Vibration Survey and Flight Flutter Test Chair: N.N. | ALTE MENSA - E.Noether Hall |
| 16:15 | 16:45 | 0231 |
Assessment of LiDAR-based techniques to measure in-flight deformation of aerospace structures J. Barrera Rodríguez, Airbus Defence & Space, ES This paper describes all the activities performed to assess the feasibility of LiDAR-based techniques for measuring the in-flight deformation of the A330-MRTT wing, together with flight test results, theoretical validation, and lesson learnt obtained. | |
| 16:45 | 17:15 | 0228 |
DORNIER SEASTAR CD2 â FLUTTER FLIGHT TEST â ADVANCED METHODS FOR IMPULSE AND NOISE BASED OMA USING NYQUIST AND SVD A. Graf, AeroFEM GmbH, CH For the flutter flight test of the next generation Dornier Seastar CD2, advanced impulse based and noise based signal processing methods for operational modal analysis (OMA) have been developed in MATLAB. The methods feature sensor arithmetic, Nyquist 2D/3D with circle fit, FFT, PSD, SVD and mode shape extraction. Flutter flight test results are successfully compared to rational flutter analysis. | |
| 17:15 | 17:45 | 0315 |
Prediction of Critical Aeroelastic Damping Using Dynamic Eigen Decomposition of Sensor Measurements J.-T. Kim, University of Washington, US Aircraft certification requires aeroelastic damping extrapolation during flight test. It conducts multiple tests at multiple flight conditions making it time-consuming, expensive and cannot predict the damping at points that have not been tested. To remedy the shortcomings a new approach is introduced using the Dynamic Eigen Decomposition of data with an artificial structural damping. |
| 11.15 Th, 18.6. 16:15 - 17:45 | Highly Flexible Aircraft Structures 3 Chair: N.N. | ALTE MENSA - Room Taberna |
| 16:15 | 16:45 | 0196 |
Co-Design of Aeroelastic Systems with Deep Reinforcement Learning Y.C. Li, Imperial College London, GB We present a model-free co-design framework that simultaneously optimises the control policy and design parameters of a fixed-wing glider for a multi-objective thermal soaring mission. The framework leverages a computationally efficient, low-fidelity flexible aircraft model developed in MuJoCo using a rigid multi-body aeroelastic formulation to facilitate training via deep reinforcement learning. | |
| 16:45 | 17:15 | 0174 |
GEOMETRIC PARAMETER-BASED SURROGATE MODELLING FOR AEROELASTIC ANALYSIS OF NOVEL AIRCRAFT CONFIGURATIONS O. Köse, HSB Solutions GmbH, DE This study presents a geometric parameter-based aerodynamic surrogate modelling approach for rapid static aeroelastic analysis of unconventional aircraft configurations. Trained on high-fidelity CFD data, the surrogates predict aerodynamic loads and their redistribution due to structural flexibility, enabling fast evaluation of aeroelastic deformation. | |
| 17:15 | 17:45 | 0237 |
RAPTOR: a gradient-based multidisciplinary design optimization framework for aircraft preliminary design J. Van Den Berghe, University of Liège, BE This work presents RAPTOR, an open-source, gradient-based multidisciplinary design optimization framework for aircraft preliminary design. The framework enables coupled aerostructural optimization. Validation against experimental data is presented, and the full paper will extend the framework to flutter analysis. |
| Th, 18.6. 17:45 - 18:00 | Room Change | 17:45 - 18:00 | ||||||
| Th, 18.6. 18:00 - 18:30 | IFASD 2026 - Closing | 18:00 - 18:30 | ||||||
| Th, 18.6. 18:30 - 18:31 | End of IFASD 2026 | 18:30 - 18:31 | ||||||
| Fr, 19.6. 09:00 - 13:00 | Technical Tour @ DLR Site Goettingen | 09:00 - 13:00 | ||||||