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Numerical solutions of the compressible 3-D boundary-layer equations for aerospace configurations with emphasis on LFCThe application of stability theory in Laminar Flow Control (LFC) research requires that density and velocity profiles be specified throughout the viscous flow field of interest. These profile values must be as numerically accurate as possible and free of any numerically induced oscillations. Guidelines for the present research project are presented: develop an efficient and accurate procedure for solving the 3-D boundary layer equation for aerospace configurations; develop an interface program to couple selected 3-D inviscid programs that span the subsonic to hypersonic Mach number range; and document and release software to the LFC community. The interface program was found to be a dependable approach for developing a user friendly procedure for generating the boundary-layer grid and transforming an inviscid solution from a relatively coarse grid to a sufficiently fine boundary-layer grid. The boundary-layer program was shown to be fourth-order accurate in the direction normal to the wall boundary and second-order accurate in planes parallel to the boundary. The fourth-order accuracy allows accurate calculations with as few as one-fifth the number of grid points required for conventional second-order schemes.
Document ID
19900003218
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Harris, Julius E. (NASA Langley Research Center Hampton, VA., United States)
Iyer, Venkit (NASA Langley Research Center Hampton, VA., United States)
Radwan, Samir (High Technology Corp. Hampton, VA., United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1987
Publication Information
Publication: Research in Natural Laminar Flow and Laminar-Flow Control, Part 2
Subject Category
Aerodynamics
Accession Number
90N12534
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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