EFFECT OF WALL TO TOTAL TEMPERATURE RATIO VARIATION ON HEAT TRANSFER TO THE LEESIDEOF A SPACE SHUTTLE CONFIGURATION AT M = 10.3

摘要

An experimental study has been conducted of the influence of wall to total temperature ratio on the heat transfer to the leeside of an 040A space shuttle configuration. The heat transfer tests were made at a Mach number of 10 and a Reynolds number of 10 per foot for angles of attack from 0° to 30°. Range of wall to total temperature ratio was from 0.16 to 0.43. Where the heat transfer was relatively high and the laminar boundary layer attached, the local heat transfer decreased by about 20 percent as the wall to total temperature ratio was increased from the minimum to the maximum test value. In regions of separated flow and vortex reattachment, very low heating rates (h/hr-1 = .001) were measured at some conditions and indicate significant changes are occurring in the leeside flow field. No single trend of heat transfer variation with wall to total temperature ratio could be observed.