Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations: Part II - Two-Dimensional Supersonic Nonadiabatic Flow and Axisymmetric Supersonic Adiabatic and Nonadiabatic Flows

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Report Number: AFFDL TR 65-107 Part 2
Author(s): Nielsen, Jack N., Lynes, Larry L., Goodwin, Frederick K.
Corporate Author(s): Itek Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1966-01
Pages: 90
Contract: AF 33(615)-1591
DoD Project: 8219
DoD Task: 821902
Identifier: AD0630765

A calculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic wall conditions. For nonadiabatic wall conditions, theories based on first-order coupling and second-order coupling between velocity and total temperature profiles were presented. The theory based on first-order coupling was included in a machine calculation program with options for two-dimensional or axisymmetric flow and adiabatic or nonadiabatic wall conditions. Extensive systematic calculations were made to determine the range of possible separated flows over a two-dimensional configuration as a function of separation point location and wall temperatures. Comparison between experiment and theory for separation pressure distributions on two -dimensional or axisymmetric adiabatic configurations shows generally good agreement.

Provenance: AFRL/VACA

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