Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow
Maurice Tucker · Stephen H. Maslen
Jan 1951 · National Advisory Committee for Aeronautics
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The analysis indicates that recovery factor decreased with increasing Mach number. For Prandtl numbers considered (0.65 to 0.75), recovery factors at stream Mach numbers of 10 were about 5 percent lower than the limiting values at zero Mach number. Reynolds number effect on recovery factor was of secondary importance. An approximation formulation that represents the computatios to within 1 percent is included for engineering calculations.
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