Im. Kalkhoran et Pm. Sforza, AIRFOIL PRESSURE MEASUREMENTS DURING OBLIQUE SHOCK-WAVE VORTEX INTERACTION IN A MACH-3 STREAM, AIAA journal, 32(4), 1994, pp. 783-788
An experimental investigation of the interaction between streamwise di
screte vortices and oblique shocks formed over a two-dimensional wedge
surface was conducted in a Mach 3 blowdown wind tunnel. An instrument
ed two-dimensional wedge section was placed downstream of a semispan w
ing so that the trailing tip vortex would arbitrarily interact with th
e shock wave formed over the wedge surface. The experiments were desig
ned to simulate interaction of streamwise vortices from upstream bodie
s with shock waves formed over aft surfaces as might be encountered in
supersonic flight of aircraft and missiles. The influence of vortex s
trength and vortex-airfoil vertical separation distance on the interac
tion was examined. The flowfield generated was found to be highly unst
eady, and a substantial change in the pressure distribution on the dow
nstream airfoil was observed. The interaction or a strong vortex with
the oblique shock wave over the downstream wedge section resulted in f
ormation of an unsteady detached shock wave upstream of the wedge lead
ing edge. Furthermore, when the vortex approached the wedge leading ed
ge, formation of a detached shock wave occurred further upstream of th
e section leading edge.