ASD Technical Report, Numéro 61

agreement angles of attack apex appears approximation body boundary layer Centerline Pressure Distributions configurations Conical Rays contoured corner cross section delta wing developed discussion Distributions Along Conical Distributions on B-W Distributions on W4 Effect of Reynolds Equivalent Cone Exact Inviscid Expansion experiment experimental figure flat flow Hypersonic improved increased indicated influenced leading edge leading-edge light Limit Lower Surface Mach 5 data Mach number method Newtonian Pressure Law noted obtained Pitch plotted plotted in Figs portion predicted presented presented in Fig pressure coefficient range Re/ft reflection region Report respectively Reynolds Number Variation seen shock layer shock-expansion shown in Fig Side similar span Spanwise Pressure Distributions Surface in Yaw Tangent Wedge theoretical theory tion tunnel two-dimensional Upper Surface Vapor Screen Photograph viscous effects W4 Lower Surface wing-body combinations zero