Simulated Thermal Protection Tile Roughness Effects on Windward Surface Heat Transfer on the Rockwell International Space Shuttle Orbiter.

摘要

Heat transfer tests on the forward half of the 0.04-scale models of the Rockwell International Space Shuttle Orbiter Configuration 140C were conducted at Mach number 8. Infrared scanning was used to determine the influence of simulated thermal protection tile roughness on windward surface heat transfer level and distribution. Tile roughness was in the form of tile surface mismatch and gaps between titles. Tile height (measured from the smooth body wall) ranged from -0.020 in. (cavity) to 0.025 in. (protuberance), and gap width ranged from 0 to 0.020 in. Data were obtained at angles of attack of 30 to 40 deg at zero side-slip at free-stream Reynolds numbers from 2,200,000 to 15,100,000 based on the total Orbiter scaled length. The infrared system is described, and data are presented which illustrate the influence of the major test parameters.