Accession Number:

AD0294192

Title:

HYPERSONIC SHOCK LAYER AT LOW REYNOLDS NUMBER. THE YAWED CYLINDER

Descriptive Note:

Corporate Author:

CORNELL AERONAUTICAL LAB INC BUFFALO N Y

Personal Author(s):

Report Date:

1962-10-01

Pagination or Media Count:

1.0

Abstract:

Low-density hypersonic flows are studied theoretically using the concept of a thin shock layer. The approach is applied to the problem of a cylinder at yaw, and to the analyses of vorticity interaction in the stagnation region for both axisymmetric and plane flows. A detailed discussion of the basic flow model is also made. Numerical solutions are obtained for yawed cylinders in the leading-edge region. The calculation encompasses a regime of rarefaction corresponding to both small and large departures from the boundary-layer solutions, and covers a range of sweep angle from 0 to 60 degrees. Solutions obtained reveal the existence of an independence principle which provides a way of correlating flow fields around cylinders at different yaw angles and Reynolds numbers. For the higher Reynolds number regime which includes the vorticity-interaction as well as the viscouslayer regimes vorticity-interaction theories based on the boundary-layer approximation are shown to be applicable in the stagnation region for both axisymmetric and plane flows. The results obtained are compared with results from other theories, and their differences are examined. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE