A modificiation to linearized theory for prediction of pressure loadings on lifting surfaces at high supersonic Mach numbers and large angles of attack
Harry W. Carlson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979 - Science - 36 pages
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Analysis of Supersonic angles of attack appendix applicability attack and high center of pressure Comparison of predicted computer program cot2 defined delta wing detailed pressure loadings edge swept 63.4 edge swept 76 effective deflection angle elliptic integral equations Experiment Linearized Experiment O Upper experimental data flow deflection angle free-stream given by linearized high angles high supersonic Mach Langley Research Center large angles leading edge swept Linearized C Modified Linearized theory Linearized linearized-theory methods linearized-theory perturbation velocities longitudinal perturbation velocity Lower surface Linearized modification to linearized Modified formulation b/2 NACA NASA nondimensional NUMBERS AND LARGE Numbers of 1.61 offer an improvement Prandtl-Meyer expansion angle predicted and measured pressure coefficient Cp pressure-coefficient formulation root chord shock detachment angle shock-expansion relationships stagnation pressure subsonic flow Subsonic leading edges supersonic flow supersonic Mach numbers surface Linearized theory surface slopes swept wing transonic Upper surface variation of pressures wing normal force wing with leading