INVESTIGATION OF SPACE SHUTTLE VEHICLE 140C CONFIGURATION ORBITER (MODEL 16-0) WHEEL WELL PRESSURE LOADS IN THE ROCKWELL INTERNATIONAL 7.75 X 11 FOOT WIND TUNNEL (0A143)

摘要

Experimental aerodynamic investigations were conducted on a sting mounted .0405-scale representation of the 140C outer mold line Space Shuttle Orbiter configuration in the Rockwell International 7.75 × 11.00 foot low speed wind tunnel during the time period from 7 to 11 November 1974. NASA designation for this test period was 0A143.nThe primary test objectives were to define the Orbiter wheel well pressure loading and its effects on landing gear thermal insulation and to investigate the pressure environment experienced by both the horizontal flight nose probe and air vent door probes. In order to accomplish the above objectives both steady state and dynamic pressure values were recorded in the Orbiter nose gear well, left main landing gear well, horizontal flight nose probe, and both left and right air vent door probe, (See Configurations Investigated).