Summary and Correlation of Skin-friction and Heat-transfer Data for a Hypersonic Turbulent Boundary Layer on Simple Shapes
Edward J. Hopkins, Morris W. Rubesin, Mamoru Inouye, Earl R. Keener, George C. Mateer, Thomas E. Polek
National Aeronautics and Space Administration, 1969 - Cone - 26 pages
Skin friction and heat transfer data for hypersonic turbulent layer on flat plates, wind tunnel wall, and cones.
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3.5-Foot Wind Tunnel adiabatic wall temperature Ames 3.5-Foot Wind Ames data Ames Research Center C0LES calculated Comparison of data Compressible flow cone Data identification data with theory directly measured distance along surface evaluate flat plates flux shear ratio Free-stream H0PKINS AND KEENER heat flux shear heat transfer heat-flux distribution heat-transfer data heat-transfer results helium High Reynolds Numbers Hopkins Hypersonic Wind Tunnel inch l0 percent laminar leading edge Mach number models momentum thickness momentum-thickness Reynolds number Morris W NACA NASA TN obtained origin of turbulent presented in figure recovery factor Reynolds analogy factor Short ref SIDE WALL skin-friction and heat-transfer skin-friction coefficient skin-friction data Skin-Friction Measurements skin-friction theories Sommer and Short Spalding and Chi STALMACH Supersonic theories of Sommer theories of Spalding thermocouple total temperature Turbulent Boundary Layer turbulent flow Turbulent Skin Friction UNPUBLISHED values Van Driest II wall data wall temperature ratios wall to adiabatic WALLACE wind-tunnel walls