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AOTV bow shock locationHypersonic bow-shock location and geometry are of central importance to the aerodynamics and aerothermodynamics of aeroassisted orbital transfer vehicles (AOTVs), but they are difficult to predict for a given vehicle configuration. This paper reports experimental measurements of shock standoff distance for the 70 deg cone AOTV configuration in shock-tunnel-test flows at Mach numbers of 3.8 to 7.9 and for angles of attack from 0 deg to 20 deg. The controlling parameter for hypersonic bow-shock standoff distance (for a given forebody shape) is the mean normal-shock density ratio. Values for this parameter in the tests reported are in the same range as those of the drag-brake AOTV perigee regime. Results for standoff distance are compared with those previously reported in the literature for this AOTV configuration. It is concluded that the AOTV shock standoff distance for the conical configuration, based on frustrum (base) radius, is equivalent to that of a sphere with a radius about 35 percent greater than that of the cone; the distance is, therefore, much less than reported in previous studies. Some reasons for the discrepancies between the present and previous are advanced. The smaller standoff distance determined here implies there will be less radiative heat transfer than was previously expected.
Document ID
19850056798
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Desautel, D.
(San Jose State University San Jose, CA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 85-1062
Accession Number
85A38949
Funding Number(s)
CONTRACT_GRANT: NCA2-OR-675-401
Distribution Limits
Public
Copyright
Other

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