ASD Technical Report, Numéro 61Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962 |
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Expressions et termes fréquents
1.0 S Spanwise angles of attack apex B1W4 Lower Surface boundary layer Centerline Pressure Distributions change in Reynolds Chordwise Pressure Distributions Comparison of Spanwise configurations Conical Coordinates Conical Rays cross section Cross-Section Pressure Distributions delta wing Distributions Along Conical Distributions on B-W Distributions on Lower Distributions on W Distributions on W4 Effect of Reynolds Exact Inviscid experimental higher angles Hyperbolic Region Hypersonic increased Limit of Hyperbolic Mach 5 data Mach number Newtonian Pressure Law nondimensional obtained outboard Photograph of B1W3 plane of symmetry plotted in Figs presented in Fig pressure coefficient pressure data pressure distribution plots pressure tests Re/ft rectangular wing Reynolds Number Variation root chord shock layer shock-expansion theory shown in Fig similar Spanwise Pressure Distributions Surface in Yaw surface pressure tangent-wedge value test program tion Vapor Screen Photograph viscous effects viscous interaction effect W4 Lower Wedge Newtonian Pressure wing W3 zero angle απ