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Aerothermal tests of a 12.5 percent cone at Mach 6.7 for various Reynolds numbers, angles of attack and nose shapesThe effects of free-stream unit Reynolds number, angle of attack, and nose shape on the aerothermal environment of a 3-ft basediameter, 12.5 deg half-angle cone were investigated in the Langley 8-foot high temperature tunnel at Mach 6.7. The average total temperature was 3300 R, the freestream unit Reynolds number ranged from 400,000 to 1,400,000 per foot, and the angle of attack ranged from 0 deg to 10 deg. Three nose configurations were tested on the cone: a 3-in-radius tip, a 1-in-radius tip on an ogive frustum, and a sharp tip on an ogive frustum. Surface-pressure and cold-wall heating-rate distributions were obtained for laminar, transitional temperature in the shock layer were obtained. The location of the start of transition moved forward both on windward and leeward sides with increasing free-stream Reynolds numbers, increasing angle of attack, and decreasing nose bluntness.
Document ID
19850009013
Document Type
Technical Publication (TP)
Authors
Nowak, R. J.
(NASA Langley Research Center Hampton, VA, United States)
Albertson, C. W.
(NASA Langley Research Center Hampton, VA, United States)
Hunt, L. R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1984
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
L-15729
NASA-TP-2345
NAS 1.60:2345
Funding Number(s)
PROJECT: RTOP 506-51-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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