Numerical Solutions for Transonic Flows Past Wing-Body Combinations
A numerical method has been developed for calculating the inviscid flow past lifting wing-body combinations by solving a form of the transonic small-perturbation equation for the velocity potential. An outline is given of the formulation of the problem and the procedure for numerical solution. Numerical results are compared with data from wind-tunnel tests on a wing-body configuration, and the variation of body interference with angle of incidence and freestream Mach number is illustrated.
KeywordsMach Number Transonic Flow Inviscid Flow Lower Mach Number Freestream Mach Number
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