The governing equations for laminar, transitional and/or turbulent, incompressible, three-dimensional boundary layers are solved numerically. The equations are developed in terms of an orthogonal surface coordinate system and include surface curvature effects. The coordinates are generated numerically, while the inviscid flow is obtained from a general potential flow procedure. The only restrictions on body geometry are that it possess a blunt nose and a plane of symmetry. The boundary-layer equations, after being transformed into similarity type variables, are solved using the implicit finite-difference Krause scheme. Various test cases are presented to establish the accuracy of the resulting computer program. (dePo)
A procedure for calculating laminar, transitional and/or turbulent, three-dimensional boundary layers including surface curvature effects about arbitrary blunt-nosed bodies
Ein Verfahren fuer die Berechnung laminarer, fluechtiger und/oder turbulenter, dreidimensionaler Grenzschichten einschliesslich der Ausiwrkung gekruemmter Flaechen auf unregelmaessige,stumpfnasige Flugkoerper
AIAA-Papers ; 1
1978
11 Seiten, 7 Bilder, 21 Quellen
Conference paper
English
Approximate Viscous Shock Layer Technique for Calculating Hypersonic Flows About Blunt-Nosed Bodies
Online Contents | 1994
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