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Aerodynamic heating on the corrugated surface of a 10.2 deg half-angle blunted cone at Mach 6.7A 10.2 deg half-angle blunted cone with corrugated surfaces was tested in the Langley 8-foot high-temperature structures tunnel to measure the aerodynamic heating of its surfaces. The tests were made in a turbulent boundary layer at angles of attack of 0 deg, 5 deg, and 10 deg. Heating of the windward side was in reasonable agreement with theoretical turbulent predictions for a smooth cone, while heating on the leeward side was between laminar and turbulent predictions as a result of local transitional flow or flow separation produced by high lee-side pressures. Localized heating measurements indicated a significant increase in heating at large cross-flow angles, with the maximum heating rates occurring where the flow reattaches on the upstream side of the corrugation crest and the minimum occurring on the downstream side where the flow is separated.
Document ID
19820005510
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Weinstein, I. (NASA Langley Research Center Hampton, VA, United States)
Avery, D. E. (NASA Langley Research Center Hampton, VA, United States)
Hunt, L. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1981
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TP-1928
L-14679
Accession Number
82N13383
Funding Number(s)
PROJECT: RTOP 506-53-63-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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