Heat-transfer and flow-field tests of the North American Rockwell/ General Dynamics Convair space shuttle configurations /
W.R. Martindale, R.K. Matthews, and L.L. Trimmer.

Description

Main Author

Martindale, W. R.

Related Names

Trimmer, L. L., author.
Matthews, R. K. (Richard K.), author.
North American Rockwell Corporation
General Dynamics Corporation. Convair Division
Arnold Engineering Development Center
United States. Air Force.
ARO, Inc.

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973.

Subjects

Aerothermodynamics.
Space shuttles > Space shuttles / Thermodynamics.

Summary

Aerothermodynamic tests of Phase B space shuttle configurations proposed by North American Rockwell/General Dynamics Convair were conducted at Mach number 8. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are: ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry including leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.

Note

Report was prepared by ARO, Inc., a subsidiary of Sverdrup & Parcel and Associates, Inc.
Final Report: June to September 1971."
"January 1973."

Physical Description

95 pages : illustrations ; 28 cm

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