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Aerodynamic heat transfer to a hypersonic research aircraft model /X-24C/ at Mach 6 (1976)

Lawing, P. L. ; Hunt, J. L.

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Publication Date: 2011-08-17

Description: The 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.

Keywords: AERODYNAMICS

Type: Journal of Aircraft; 13; Dec. 197

Format: text

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