## A simple integral method for the calculation of real-gas turbulent boundary layers with variable edge entropyCharles B. Johnson, Lillian R. Boney, United States. National Aeronautics and Space Administration, Langley Research Center Simple integral method for calculating real gas turbulent boundary layers with variable edge entropy and flight calculations showing effect of nose bluntness at 6.09 km/sec. |

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approximately boundary-layer calculation change in entropy culations dimensionless displacement thickness Driest II ref edge conditions effect of nose effect of three end of transition enthalpy equilibrium air Fc function final calculation final iteration final laminar entropy final turbulent calculation flat plate flow properties ft/sec given in reference half-angle cone heat transfer heat-transfer data hw/He Hypersonic initial value inviscid solution km/sec laminar entropy distribution laminar flow Langley Research Center Mach number Mangler transformation factor momentum thickness N-power NASA TN nose bluntness nose radius Prandtl number ratio real-gas Reynolds analogy factor Reynolds number based sharp-cone value shown in figure SIMPLE INTEGRAL METHOD skin friction skin-friction coefficient solution for laminar Spalding-Chi ref Spalding-Chi skin-friction theory Spalding-Chi theory Stanton number thermodynamic three entropy distributions three turbulent-boundary-layer tion transition region turbulent boundary layer turbulent flow turbulent-boundary-layer calculations U.S. Customary Units U.S. Navy value of Cf/2 variable entropy variation velocity profiles