Pressure and Heat Transfer Tests on the NASA Space Shuttle External Tank at Mach Number 16

An experimental test program was conducted in the AEDC-VKF Hypervelocity Wind Tunnel F at a nominal Mach number of 16 to obtain basic heating and pressure distribution data on the NASA Space Shuttle external tank. The tests were conducted over an attitude range which simulated tank tumbling after separation from the Shuttle orbiter. The angles of attack varied from 0 to -180 deg with combinations of roll from 0 to 90 deg at free-stream Reynolds numbers based on model length from 0.38 x 1,000,000 to 1.10 x 1,000,000. In addition to surface heat-transfer gages, thermographic phosphor paint was used to determine the interference heating factors on and around the various attachment structures and service ducts.