A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-Speed Aircraft

Quinn, Robert D. and Gong, Leslie (2000) A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-Speed Aircraft. Technical Report NASA/TP-2000-209034, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.

EPrint Type:	NASA Technical Publication
Keywords:	Aerodynamic heating, Boundary layer, Flight measurements, Flow hypersonic, Flow inviscid
Subjects:	(31 - 39) Engineering: (34) Fluid Mechanics and Thermodynamics Aircraft/Project: YF-12 Aircraft/Project: X-15 Aircraft/Project: Space Shuttle Orbiter
ID Code:	83
Deposited On:	12 July 2004
Additional Information:	35 pages. Robert D. Quinn, Analytical Services and Materials, Inc., Edwards, California; Leslie Gong, NASA Dryden Flight Research Center, Edwards, California.