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An empirical method for computing leeside centerline heating on the Space Shuttle OrbiterAn empirical method is presented for computing top centerline heating on the Space Shuttle Orbiter at simulated reentry conditions. It is shown that the Shuttle's top centerline can be thought of as being under the influence of a swept cylinder flow field. The effective geometry of the flow field, as well as top centerline heating, are directly related to oil-flow patterns on the upper surface of the fuselage. An empirical turbulent swept cylinder heating method was developed based on these considerations. The method takes into account the effects of the vortex-dominated leeside flow field without actually having to compute the detailed properties of such a complex flow. The heating method closely predicts experimental heat-transfer values on the top centerline of a Shuttle model at Mach numbers of 6 and 10 over a wide range in Reynolds number and angle of attack.
Document ID
19810054653
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Helms, V. T., III
(NASA Langley Research Center Space Systems Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 81-1043
Meeting Information
Meeting: Thermophysics Conference
Location: Palo Alto, CA
Start Date: June 23, 1981
End Date: June 25, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A39057
Distribution Limits
Public
Copyright
Other

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