An overview is presented of unsteady inviscid calculation methods at the National Aerospace Laboratory (NLR), which are primarily based on the full potential equation for the prediction of airloads on oscillating structures in transonic flow. Attention is given to experience with entropy/vorticity corrections and a procedure which removes the frequency barrier associated with time-linearized modelings. This procedure has a favorable effect on computer cost such that transonic flutter boundaries can be obtained in acceptable turn-around times on current workstations. A method for transonic aeroelastic analysis of complete aircraft which is now in the stage of development is introduced, and attention is given to its grid generation procedure. The methods are demonstrated by showing results of unsteady loads and pressure coefficients applications in 2D and 3D transonic flow and an aeroelastic application to a 3D AGARD standard aeroelastic case in transonic flow.
NLR Inviscid Transonic Unsteady Loads Prediction Methods in Aeroelasticity
1992
16 pages
Report
No indication
English