VOLUME 3 OF 3 TEST RESULTS FROM THE NASA/ROCKWELL INTERNATIONAL SPACE SHUTTLE 0.0175-SCALE ORBITER MODELS 56-0/60-0 AND 0.04-SCALE ORBITER FOREBODY MODEL 83-0 CONDUCTED IN THE AEDC/VKF-Bn50-INCH HYPERSONIC WIND TUNNEL (TESTS OH109 AND OH109B)

摘要

Orbiter Heating Test, OH109, was conducted using scaled Space Shuttle Orbiter models at the Arnold Engineering Development Center's Von Karman Facility (AEDC-VKF) Hypersonic Wind Tunnel B, to obtain additional aerodynamic heating data in finer detail than previously tested for Orbiter STS-1 entry yaw angles. The test program utilized three Rockwell International models: the 0.0175 scale 56-0 and 60-0, and the 0.04 scale 83-0.nData were recorded at yaw angles of 0, +0.5, +1.0 and +2.0 degrees at angles of attack of 20, 25, 27.5, 30, 32.5, 35, and 40 degrees. Nominal Mach number was 8.0 and Reynolds number (x 106 /ft) values were 0.5, 1.0, 2.0, 3.0, and 3.7. In addition to the required yaw heating objectives, oil flow tests were conducted on the 83-0 model and the 60-0 model, with eleven deflections of 0 and 5 degrees.nA phase-change paint test was added on to the OH109 test program and designated OH109B. The objective of the phase-change paint test was to establish the peak heating location for the SILTS pod located on the orbiter vertical tail. This portion of the test was performed on the 56-0 model (See Table VII).