G.N. Dudin  , V.Ya. Neyland

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_1070895

Laminar boundary layer flow over an infinite-span, finite-length flat plate is investigated in the regime of strong interaction with a hypersonic gas flow. Under the assumption that an additional condition dependent on the transverse coordinate can be imposed on the trailing edge of the plate the flow functions are expanded in power series in the vicinity of the leading edge. It is shown that these expansions include an indefinite function dependent on the transverse coordinate. Two boundary value problems are formulated. One of them serves for determining the flow functions in the selfsimilar case. The other problem makes it possible to calculate the eigenvalue characterizing the intensity of the upstream transfer of disturbances and to determine the coefficients for the subsequent terms of the expansion. It is established that in this case the two-dimensional boundary layer can rearrange itself into a three-dimensional boundary layer.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Aerodynamics, Transition to Turbulence
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