Effect of Shock Impingement on Heat Transfer. Part IV. A Further Experimental and Theoretical Investigation of Adiabatic Laminar Boundary Layer/Shock Wave Interactions on Curved Walls.
Final scientific rept. 1 May 71-31 Dec 75,
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
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A theoretical parametric study has been made of adiabatic, laminar boundary layershock wave interactions on flat plateconvex ramp configurations. The ramp takes the form of a circular arc. This was done by using a computer program based on the integral method of Lees and Reeves recently successfully modified to include effects of streamwise ramp curvature. Primarily, the effects of different ramp radii on the overall interaction pressure distribution and other salient interaction parameters have been studied. As a further check on the theoretical model, which has already been successfully compared with experimental results at low Mach numbers, static pressure distributions throughout adiabatic laminar interactions have been measured at a free stream Mach number of 5.55. Compared to the present measured pressure distributions the theoretical model gives a satisfactory comparison downstream of the corner but overpredicts the extent of upstream influence. Furthermore, experimental pressure distributions are presented of adiabatic transitional interactions generated on convex ramp models. Author
- Fluid Mechanics