Analysis of the Three-Dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow
Final rept. Jul 71-Feb 72,
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An analytical approach toward numerical calculation of the three- dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three- dimensional turbulent boundary-layer equations in conjunction with a three- dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure velocity and temperature profiles, the surface streamline direction obtained via an oil-flow technique and surface heat-transfer rate.
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