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Thin-layer approximation and algebraic model for separated turbulent flowsAn algebraic turbulence model for two- and three-dimensional separated flows is specified that avoids the necessity for finding the edge of the boundary layer. Properties of the model are determined and comparisons made with experiment for an incident shock on a flat plate, separated flow over a compression corner, and transonic flow over an airfoil. Separation and reattachment points from numerical Navier-Stokes solutions agree with experiment within one boundary-layer thickness. Use of law-of-the-wall boundary conditions does not alter the predictions significantly. Applications of the model to other cases are contained in companion papers.
Document ID
19780036867
Document Type
Conference Paper
Authors
Baldwin, B. (NASA Ames Research Center Moffett Field, CA, United States)
Lomax, H. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number
AIAA PAPER 78-257
Meeting Information
Aerospace Sciences Meeting(Huntsville, AL)
Distribution Limits
Public
Copyright
Other