An overview is presented of unsteady inviscid calculation methods developed at 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 the transonic aeroelastic analysis of complete aircraft which is currently in the stage of development will be 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 2-D and 3-D transonic flow and of an aeroelastic application to a 3-D AGARD standard aeroelastic case in transonic flow.
NLR Inviscid Transonic Unsteady Loads Prediction Methods in Aeroelasticity (December 1991)
1991
23 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Computational fluid dynamics , Transonic flow , Unsteady flow , Aerodynamic loads , Aeroelasticity , Supercritical wings , Computational grids , Vortices , Pressure distribution , Oscillating flow , Unsteady aerodynamics , Airfoils , Aerodynamic configurations , Entropy , Transonic flutter , Grid generation(Mathematics) , Foreign technology