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On Supersonic Flow About Slender Bodies of Elliptic Cross Section by C H
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aerodynamic Aeronautical Sciences aircraft airfoil analysis angle of attack applied approximation assumed assumption axial blade body of revolution boundary conditions buckling calculated cascade cent compressible compressible flow cone constant coordinates corresponding curve determined differential equation displacement thickness dp/dx drag effect energy equilibrium experimental flat plate fluid free-stream friction coefficient function given heat transfer integral investigation Journal laminar boundary layer leading edge leading-edge lift linear load Mach Number Mach waves measured method momentum NACA TN nozzle obtained parameters pitot tube plane plastic plotted Prandtl Number present pressure distribution pressure gradient problem ratio recovery factors reference region Reynolds Number shear stress shock wave shown in Fig skin friction solution sonic stream function stringers subsonic Supersonic Flow surface temperature theoretical theory thickness tion tube tunnel turbulent boundary layer two-dimensional values variable variation velocity potential velocity profiles vortex wall wing wing-body zero