An aeroelastic dataset generation method for aircraft, which is based on coupled CFD-CSM simulations and a Chimera approach for control surfaces is presented. It is embedded in the multidisciplinary simulation environment SimServer. The DLR TAU code is employed to obtain the CFD solution by solving the Reynolds-Averaged Navier-Stokes equations. Structural displacements are computed with a modal solver. The aeroelastic dataset production method is applied to the Northrop F-5A aircraft. A CAD surface model of the aircraft and a structural model has been generated and are introduced. Numerical simulations are performed at transonic speed (formula presented) = 0.89, a flight altitude of ℎ = 10668 m and several angles of attack (formula presented) . Control surface deflections of the leading edge flap, trailing edge flap, aileron and horizontal stabilizer are considered. The effect of control surface deflections on the force and moment coefficients are analyzed. The influence of flexibility on the configuration is evaluated by comparing the force and moment coefficients of the aeroelastic simulations to the aerodynamic simulations, where the aircraft is assumed to be fully rigid. A comparison of the results obtained by aerodynamic and aeroelastic simulations show that the flexibility of the aircraft influences the lift, pitching moment and rolling moment coefficient for all considered angles of attack. © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.     «

An aeroelastic dataset generation method for aircraft, which is based on coupled CFD-CSM simulations and a Chimera approach for control surfaces is presented. It is embedded in the multidisciplinary simulation environment SimServer. The DLR TAU code is employed to obtain the CFD solution by solving the Reynolds-Averaged Navier-Stokes equations. Structural displacements are computed with a modal solver. The aeroelastic dataset production method is applied to the Northrop F-5A aircraft. A CAD surf...     »