## A Modification to Linearized Theory for Prediction of Pressure Loadings on Lifting Surfaces at High Supersonic Mach Numbers and Large Angles of Attack |

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Analysis of Supersonic angles of attack appendix applicability attack and high center of pressure Comparison of predicted cot2 defined delta wing edge swept 63.4 edge swept 76 effective deflection angle effective expansion elliptic integral equations equivalent turning angle Experiment Linearized theory Experiment O Upper experimental data flow deflection angle given by linearized high angles high supersonic Mach Isentropic 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 oblique-shock offer an improvement Prandtl-Meyer expansion angle predicted and measured pressure-coefficient formulation root chord shock detachment angle shock-expansion relationships stagnation pressure subsonic flow Subsonic leading edges supersonic flow supersonic Mach numbers surface D Lower surface Linearized theory surface slopes swept wing transonic Upper surface variation of pressures wing normal force wing with leading