Space Shuttle orbiter entry heating and TPS response: STS-1 predictions and flight data
Abstract
Aerothermodynamic development flight test data from the first orbital flight test of the Space Transportation System (STS) transmitted after entry blackout is given. Engineering predictions of boundary layer transition and numerical simulations of the orbiter flow field were confirmed. The data tended to substantiate preflight predictions of surface catalysis phenomena. The thermal response of the thermal protection system was as expected. The only exception is that internal free convection was found to be significant in limiting the peak temperature of the structure in areas which do not have internal insulation.
- Publication:
-
Computational Aspects of Heat Transfer in Structures
- Pub Date:
- 1982
- Bibcode:
- 1982caht.nasa..327R
- Keywords:
-
- Aerodynamic Heating;
- Heat Transfer;
- Reentry Effects;
- Space Shuttle Orbiters;
- Space Transportation System 1 Flight;
- Spacecraft Reentry;
- Boundary Layer Transition;
- Catalysis;
- Free Convection;
- Reusable Heat Shielding;
- Surface Temperature;
- Thermal Insulation;
- Thermal Protection;
- Fluid Mechanics and Heat Transfer