University of North Texas Digital Library (University of North Texas) · 1957 · 67 citations · 0 references
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EngineeringAerospace EngineeringAerodynamicsDifferential EquationsFluid DynamicsAirfoil TheoryComputational AerodynamicsSubsonic AerodynamicsSupersonic AerodynamicsTransonic AerodynamicsUnsteady AerodynamicsFlow Over AirfoilsMach NumberSupersonic AirfoilsSupersonic FlowThin Airfoil TheoryTransonic AirfoilsTransonic FlowTransonic Pressure Distributions
A method is presented for the approximate solution of the nonlinear equations transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed pressure distribution. Extensive comparisons are made with available data, particularly for a Mach number of 1, and with existing solutions.