Aerodynamic heating phase change paint tests for the space shuttle orbiter are reported. The model was a 0.040 scale representation of the forward 50% of the orbiter. Surface roughness effects on boundary layer transition were investigated. The roughness was simulated by steel balls 0.020 and 0.025 inch in diameter and a 0.25 in. diameter hole simulating the forward ET attach socket. A nominal Mach number of was tested with unit Reynolds number varying from 0.75 x 1 million ft through 3.5x 1 million ft. Angle of attack was varied from 20 degrees to 40 degrees.
Results of Phase Change Paint Heat Transfer Test Utilizing 0.040-Scale 50% Forebody Models (No. 82-0) of the Rockwell International Space Shuttle Orbiter in AEDC Vkf Hypersonic Tunnel B (Test Oh54b)
1977
70 pages
Report
Keine Angabe
Englisch