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A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings

Author
Cebeci, T.
Published
Jan 1, 1977.
Physical Description
1 electronic document
Additional Creators
Kaups, K. and Ramsey, J. A.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The method described utilizes a nonorthogonal coordinate system for boundary-layer calculations. It includes a geometry program that represents the wing analytically, and a velocity program that computes the external velocity components from a given experimental pressure distribution when the external velocity distribution is not computed theoretically. The boundary layer method is general, however, and can also be used for an external velocity distribution computed theoretically. Several test cases were computed by this method and the results were checked with other numerical calculations and with experiments when available. A typical computation time (CPU) on an IBM 370/165 computer for one surface of a wing which roughly consist of 30 spanwise stations and 25 streamwise stations, with 30 points across the boundary layer is less than 30 seconds for an incompressible flow and a little more for a compressible flow.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19770010051.
Accession ID: 77N16994.
NASA-CR-2777.
Terms of Use and Reproduction
No Copyright.
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