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Computational Results and Comparisons With WindTunnel Aeroheating and Aerodynamic Data
4E6/ft Test aerodynamic aeroheating predictions Air Tunnel angles of attack axial cuts Baldwin-Lomax model body-flap deflections boundary layer bow shock bowed panel models chine coefficient with Mach coefficients for Langley computation versus heating computations were performed Computed lateral Computed variation computed with GASP cuts from X/L cuts to X/L data on bowed data on smooth depiction of GASP distribution for flight experimental data experimental heating data Free-Stream Conditions GASP laminar computation GASP laminar solution GASP turbulent computation GASP turbulent solution Graphical depiction heat transfer coefficient Horvath hypersonic laminar computation versus Langley 20-Inch Mach Langley Research Center LAURA lift-to-drag ratio Mach 6 Air Mach 6 wind-tunnel Mach number Measured and predicted models at Mach models with trips NASA normal force number and angle percent Re_inf Reynolds number smooth models solution and experimental solution and heating surface streamlines surface temperature distribution turbulent computation versus versus heating data wind-tunnel conditions X-33 vehicle