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in supersonic wind tunnel of the Jet Propulsion Laboratory
On the Structure of Jets From Highly Underexpanded Nozzles Into Still
66 other sections not shown
aerodynamic Aeronautical Sciences aircraft airfoil analysis angle of attack applied approximation assumed axial axis body of revolution boundary conditions calculated coefficient compressible computed constant coordinates corresponding curve cylinder delta wing determined differential equation drag drag coefficient effect energy experimental flat plate flight flow field fluid force free-stream function given gradient gust heat addition heat transfer heat-transfer Hypersonic integral investigation Journal Laminar Boundary Layer leading edge linear load Mach Number method motion NACA NACA TN nondimensional nonlinear normal nose nozzle obtained orbit parameter plane present pressure distribution problem Propulsion ratio reference region relation Reynolds Number shear shock tube shock wave shown in Fig solution sonic speed stagnation point subsonic supersonic supersonic flow surface temperature theoretical theory thermal thickness tion trajectory transonic tube turbulent two-dimensional variable variation velocity vertical viscous vortex wall wind tunnel wing zero