EXPERIMENTAL INVESTIGATION OF THE INTERACTION OF A PLANE, OBLIQUE, INCIDENT-REFLECTING SHOCK WAVE WITH A TURBULENT BOUNDARY LAYER ON A COOLED SURFACEnVOLUME 1: TEST DESCRIPTION AND DATA SUMMARY

摘要

A test was conducted to obtain measurements of the boundary layer total temperature and velocity profiles in the region of the interaction of a two-dimensional, incident, reflecting, oblique shock wave with the turbulent boundary layer on a cryogenically cooled flat plate. Data were taken at Mach numbers of 2.0, 3.2and 4.2 at unit Reynolds numbers of from 6.4 to 20.2 million per foot. The ratio of wall surface to stagnation tem perature was 0.3 for most data. Adiabatic data were taken at a Mach number of 3.2. Incident shock strength was varied by testing with shock generator wedge angles of 6° and 8°. Data presented include the plate surface-pressure distribution, incident and reflected shock locations, and the boundary layer velocity and stagnation temperature profiles.