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Aerothermal test results from the first flight of the Pegasus air-launched space boosterA survey of temperature measurements at speeds through Mach 8.0 on the first flight of the Pegasus air-launched booster system is discussed. In addition, heating rates were derived from the temperature data obtained on the fuselage in the vicinity of the wing shock interaction. Sensors were distributed on the wing surfaces, leading edge, and on the wing-body fairing or fillet. Side-by-side evaluations were obtained for a variety of sensor installations. Details of the trajectory reconstruction through first-stage separation are provided. Given here are indepth descriptions of the sensor installations, temperature measurements, and derived heating rates along with interpretations of the results.
Document ID
19920002083
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Noffz, Gregory K. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Curry, Robert E. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Haering, Edward A., Jr. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Kolodziej, Paul (NASA Ames Research Center Moffett Field, CA., United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-4330
H-1672
NAS 1.15:4330
Accession Number
92N11301
Funding Number(s)
PROJECT: RTOP 505-59-40
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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