Linearized compressible-flow theory for sonic flight speeds

Max A. Heaslet, Harvard Lomax, John R. Spreiter
naca-tn-1824
Jan 1950


The partial differential equation for the perturbation velocity potential is examined for free-stream Mach numbers close to and equal to one. It is found that, under the assumptions of linearized theory, solutions can be found consistent with the theory for lifting-surface problems both in stationary three-dimensional flow and in unsteady two-dimensional flow. Several examples are solved including a three-dimensional swept-back wing and a two-dimensional harmonically oscillating wing, both for a free-stream Mach number equal to one.

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