HEAT TRANSFER TESTS OF AN 0.006-SCALE THIN SKIN SPACE SHUTTLE THERMOCOUPLE MODEL (41-0) IN THE LANGLEY RESEARCH CENTER VARIABLE DENSITY TUNNEL AT M = 8 (OH13)

摘要

This report presents data obtained from heat transfer tests on an 0.006-scale, Space Shuttle Orbiter Vehicle in the Langley Research Center,nVariable Density, Mach 8 Wind Tunnel. The purpose of/this test was to obtain orbiter entry heating distributions and to correlate phase change paint data with thermocouple data. The orbiter was tested at 0, 30, and 35 degrees angle of attack at Reynolds numbers of 1, 2, 3, 4, and 6 million per foot. Temperature data were obtained from a total of 57 thermocouples.