Publication Date:
2019-07-13
Description:
The entry aerothermodynamic environment for the Space Shuttle vehicle was an important factor in the design of the Orbiter. A design goal established during the initial study phase of the Shuttle program was to minimize the thermal protection system's weight. A description is presented of the design approach and preliminary flight test results relative to the entry heating environment for the complex flowfield regions of the Space Shuttle Orbiter. Attention is given to Orbiter aerothermodynamic design features, aspects of trajectory development, the wind tunnel test program, heating environments, boundary-layer transition problems, and the flight test program.
Keywords:
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 82-0821
,
Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
Format:
text
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