RESEARCH ON EVAPORATIVE FILM COOLING OF A MACH NUMBER 7 CONTOURED WIND TUNNEL NOZZLE IN THE ROSEMOUNT AERONAUTICAL LABORATORIES' HYPERSONIC FACILITY

摘要

An experimental research program on evaporative film cooling of a Mach number 7 Laval nozzle was conducted in the 12 x 12-inch test section of the hypersonic blow down wind tunnel at the Rosemount Aeronautical Laboratories. Coolant (water) was injected through a thin strip of porous stainless steel plate located upstream of the nozzle throat where the average Mach number was 0.10. The object of this investigation was to analyze the influence of evaporative film cooling on the potential flow area available for model testing. For this purpose, a transverse pitot pressure and total tempera¬ture survey was performed in the uniform flow region of the test section. Impact pressure and total temperature measurements were made in the turbu¬lent boundary layer on the wall at the nozzle exit v/here M = 7 with stagnation temperatures up to 2040 R. The results are compared to a former inves¬tigation of evaporative film cooling in a throat section of a hypersonic nozzle.