Theoretical investigation of 3D shock waveturbulent boundary layer interactions, part 7
Abstract
This research describes continuing efforts in the analysis of 3D shock wave turbulent boundary layer interactions. A significant research activity in 3D hypersonic shock turbulent interactions is initiated to further develop and validate the theoretical model. The quasiconical free interaction principle is examined by simulation of two geometries 17.5 deg sharp fin and (30,60) swept compression corner (Mach 3)  selected to obtain similar shock strengths. The comparison with experimental data is good. It is confirmed that the differences caused by the particular geometry of the model appear only behind the inviscid shock wave. Continuing research on 3D turbulent interaction control is focused on the effect of bleed and the simulation of flows past the doublefin configuration. The effect of suction is examined on a strong (fin angle = 20 deg, Mach 3) and a weak interaction (8 deg, Mach 3). The overall effect of bleed is remarkably modest. Two doublefin configurations (4 x 4 and 8 x 8, Mach 3) are simulated. A study of the computed flowfield indicates that the first is a weak interaction. In contrast, the 8 x 8 configuration displays an interesting separated flowfield. An analysis of viscous and inviscid effects in a sharp fin and a swept corner flow indicates that the physics of both geometries are governed primarily by inviscid (pressure) effects. Viscous effects are of lower magnitude but are not restricted to the sublayer region.
 Publication:

Annual Report
 Pub Date:
 November 1988
 Bibcode:
 1988rsu..reptT....K
 Keywords:

 Compressible Boundary Layer;
 Computational Fluid Dynamics;
 Flow Theory;
 Mathematical Models;
 Mechanical Properties;
 NavierStokes Equation;
 Shock Wave Interaction;
 Fins;
 Flow Distribution;
 High Speed;
 Inviscid Flow;
 Shock Layers;
 Simulation;
 Viscous Flow;
 Fluid Mechanics and Heat Transfer