NASA NTRS · 19930090934
Linearized compressible-flow theory for sonic flight speeds
Abstract
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 two dimensional harmonically-oscillating wing, both for a free stream Mach number equal to one. Momentum relations for the evaluation of wave and vortex drag are also discussed. (author)
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Heaslet, Max A, Lomax, Harvard, Spreiter, John R. 1950-01-01. Linearized compressible-flow theory for sonic flight speeds. https://ntrs.nasa.gov/citations/19930090934
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