ENTRY HEAT TRANSFER TESTS OF THE 0.006-SCALE SPACE SHUTTLE (-147B) ORBITER MODEL (50-0) IN THE LANGLEY RESEARCH CENTER FREON TUNNEL AT MACH 6(0H45)

摘要

Presented herein are results of heat transfer tests of a 147B configuration orbiter model (50-0) conducted in the NASA Langley Research Center Freon Tunnel (LRC/CF4). These tests were conducted at a nominal. Mach number of 6, and at Reynolds numbers of 0.3 and 0.5 × 10 per foot. The objectives of.-the tests were to determine the effects of the low freon specific heat ratio, γ on the heating distributions and to determine the impingement of the orbiter bow shock on the wing.nThe data presented include thin skin heat transfer data (tabulated data and plotted data).