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Aerodynamic heating and loading within large open cavities in cone and cone-cylinder-flare models at Mach 6.7The aerodynamic heating and loading distributions within large cavities exposed by surface openings to hypersonic flow were determined in the 8-foot high-temperature structures tunnel. Cone and cone-cylinder-flare models with cavities having regular and irregular surface-opening shapes were aerothermally tested at various angles of attack up to 30 deg. Tests were conducted at a Mach number of 6.7, a total temperature of 1800 K, a dynamic pressure of 80 kPa, and a stream unit Reynolds number of 6,000,000 per meter. The results showed that the heating rates at internal reattachment were generally lower but of the same order as the corresponding external heating rates; however, other internal heating rates were an order of magnitude lower. The internal flow showed characteristics of being funneled into jets or being dispersed dependent upon the internal surface contour.
Document ID
19740010445
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Hunt, R. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
L-9157
NASA-TN-D-7403
Accession Number
74N18558
Funding Number(s)
PROJECT: RTOP 760-17-01-15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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