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Aerodynamic heat transfer to a hypersonic research aircraft model /X-24C/ at Mach 6The paper reports on results of heat-transfer tests conducted on a 1/29-scale model of the X-24C-12I hypersonic research aircraft configuration in a Mach 6 tunnel at a Reynolds number of thirteen million using the phase-change heat transfer technique. Sequences of phase-change heat transfer pattern photographs are presented showing windward side and leeward side heating processes. Theoretical predictions of dimensionless heat transfer coefficients along a data line on lower fuselage and on fuselage side bracket the experimental values. A turbulent heating theory gives good agreement with data when shifted to a new virtual origin.
Document ID
19770031705
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lawing, P. L.
(NASA Langley Research Center Hampton, VA, United States)
Hunt, J. L.
(NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
December 1, 1976
Publication Information
Publication: Journal of Aircraft
Volume: 13
Subject Category
Aerodynamics
Accession Number
77A14557
Distribution Limits
Public
Copyright
Other

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