Flowfield and vehicle parameter influence on hypersonic heat transfer and drag
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[1] John C. Adams,et al. Implicit Finite-Difference Analysis of Compressible Laminar, Transitional, and Turbulent Boundary Layers along the Windward Streamline of a Sharp Cone at Incidence , 1971 .
[2] V. Vatsa,et al. Navier-Stokes computations of a prolate spheroid at angle of attack , 1989 .
[3] Richard A. Thompson,et al. Viscous shock-layer solutions with nonequilibrium chemistry for hypersonic flows past slender bodies , 1989 .
[4] P. C. Stainback,et al. Effect of unit Reynolds number, nose bluntness, angle of attack, and roughness on transition on a 5 deg half-angle cone at Mach 8 , 1969 .
[5] R. A. Thompson. Comparison of nonequilibrium viscous-shock-layer solutions with windward surface Shuttle heating data , 1987 .
[6] P. Libby,et al. Analysis of Turbulent Boundary Layers , 1974 .
[7] R. Davis,et al. Numerical solution of the hypersonic viscous shock-layer equations , 1970 .
[8] J. Muir,et al. Experimental investigation of the effects of nose bluntness, free-stream unit Reynolds number, and angle of attack on cone boundary layer transition at a Mach number of 6 , 1972 .
[9] Clark H. Lewis,et al. Hypersonic Three-Dimensional Viscous Shock-Layer Flows over Blunt Bodies , 1978 .
[10] Tuncer Cebeci,et al. Behavior of turbulent flow near a porous wall with pressure gradient , 1970 .
[11] Kenneth F. Stetson. Hypersonic Laminar Boundary Layer Transition. Part 1. Nosetip Bluntness Effects on Cone Frustum Transition. Part 2. Mach 6 Experiments of Transition on a Cone at Angle of Attack , 1982 .
[12] Clark H. Lewis,et al. Chemical equilibrium laminar or turbulent three-dimensional viscous shock-layer flows , 1983 .
[13] M. Holden. Experimental studies of the effects of asymmetric transition on the aerothermal characteristics of hypersonic blunted slender cones , 1985 .
[14] Kathryn E. Wurster,et al. Aerothermodynamic study of slender conical vehicles , 1987 .
[15] Peter A. Gnoffo,et al. Enhancements to Program LAURA for computation of three-dimensional hypersonic flow , 1987 .
[16] Richard A. Thompson,et al. Viscous shock-layer solutions with nonequilibrium chemistry for hypersonic flows past slender bodies , 1988 .
[17] D. Chaussee,et al. An upwind algorithm for the parabolized Navier-Stokes equations , 1986 .
[18] G. Widhopf. Turbulent HeatmTransfer Measurements on a Blunt Cone at Angle of Attack , 1971 .
[19] A. Martellucci,et al. The influence of asymmetric transition on re-entry vehicle motion , 1970 .
[20] I. E. Beckwith,et al. A survey of NASA Langley studies on high-speed transition and the quiet tunnel , 1972 .
[21] Stanley Osher,et al. Application of a new class of high accuracy TVD schemes to the Navier-Stokes equations , 1985 .
[22] G. Rushton,et al. Shock tunnel investigation of boundary-layer transition at M equals 5.5. , 1966 .
[23] Kam-Pui Lee,et al. Viscous shock-layer analysis of hypersonic flows over long slender bodies , 1987 .
[24] Roddam Narasimha,et al. Some properties of boundary layer flow during the transition from laminar to turbulent motion , 1958, Journal of Fluid Mechanics.
[25] W. Moeckel. Some effects of bluntness on boundary-layer transition and heat transfer at supersonic speeds , 1956 .