An experimentalcomputational investigation of transonic shock waveturbulent boundary layer interaction in a curved test section
Abstract
A transonic shock waveturbulent boundary layer interaction was studied in a curved test section in which the flow was computed by a 2D Euler flow method. The flow field near the shock wave at the convex wall corresponds to that near the shock wave at the upper surface of a transonic airfoil. The Mach number distributions from the Euler flow computations are compared to those obtained from holographic interferometry, at flow Mach numbers upstream of the shock wave of 1.15 and 1.37. At both Mach numbers the streamline curvature leads to a supersonic region downstream of the shock wave. Relying on the Euler flow computations this must be attributed to viscous effects. Surface curvature and the adverse pressure gradient induce, compared to flat plate experiments without adverse pressure gradient, an increase of the boundary layer displacement thickness and of the shape factor. No increase of the separation length is measured with respect to experiments at noncurved surfaces. The separation criterion of ALBER et al. (1971) agrees with the present findings; this does not apply to the reattachment criterion.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 July 1987
 Bibcode:
 1987STIN...8821408N
 Keywords:

 Airfoil Profiles;
 Computational Fluid Dynamics;
 Shock Wave Interaction;
 Transonic Flow;
 Turbulent Boundary Layer;
 Wind Tunnel Tests;
 Boundary Layer Separation;
 Flow Distribution;
 Mach Number;
 Fluid Mechanics and Heat Transfer