HEAT TRANSFER PHASE CHANGE PAINT TESTS OF 0.0175-SCALE MODELS (NOS. 21-0 AND 46-0) OF THE ROCKWELL INTERNATIONAL SPACE SHUTTLE ORBITER IN THE AEDC TUNNEL B HYPERSONIC WIND TUNNEL (TEST 0H25A)

摘要

Tests were conducted in the AEDC-VKF Hypersonic Wind Tunnel (B) using various truncated space shuttle Orbiter configurations in an attempt to establish the optimum model size for later tests examining body shock-wing leading edge interference effects. The tests were conducted at Mach number 8 using the phase change paint technique. A test description, tabulated data, and tracings of isotherms made from photographs taken during the test are presented.