NASA NTRS · 19870000029
Improved Heat-Transfer Calculations for Hypersonic Flow
Abstract
Lewis number corrected for extremely high airspeeds. Algorithm calculates improved, variable value of Lewis number, factor in equation for heat-transfer coefficient at stagnation point of body in hypersonic flow mach numbers of approximately 25. New algorithm improves accuracy of calculations of heat generated by hot air acting on moving body.
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Greenschlag, S. N.. 1987-01-01. Improved Heat-Transfer Calculations for Hypersonic Flow. https://ntrs.nasa.gov/citations/19870000029
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