An experimental investigation of the interaction between streamwise discrete vortices and oblique shocks formed over a two-dimensional wedge surface was conducted in a Mach 3 blowdown wind tunnel. An instrumented two-dimensional wedge was placed downstream of a semiispan wing so that the trailing tip vortex would arbitrarily interact with the shock wave formed over the wedge surface. The experiments were designed to simulate interaction of streamwise vortices from upstream bodies with shock waves formed over aft surfaces as might be encountered in supersonic flight of aircraft and missiles. The influence of vortex strength and vortex-airfoil vertical separation distance on the interaction was examined.
Airfoil pressure measurements during oblique shcok-wave/vortex interaction in a Mach 3 stream
AIAA Journal ; 32 , 4
1994-04-01
Miscellaneous
No indication
English
Airfoil Pressure Measurements During Oblique Shock-Wave-Vortex Interaction in a Mach 3 Stream
Online Contents | 1994
|Vortex distortion during vortex-surface interaction in a Mach 3 stream
Tema Archive | 1994
|