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A Reference-Plane Method for the Solution of Three-Dimensional Supersonic Flows

Published online by Cambridge University Press:  07 June 2016

R Camarero
R Camarero*
Affiliation:
University of Sherbrooke, Quebec
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Summary

A numerical method for the solution of three-dimensional supersonic flows and the associated computer programme have been devised. The present algorithm is based on a reference-plane characteristic network. The physical region between the shock wave and the body surface is replaced by a computational mesh facilitating the incorporation of different boundary conditions and arbitrary body shapes. For reasons of stability and computing time a Hartree-type grid was used where the characteristic segments are projected upstream. The base points do not coincide with nodal points and interpolation by means of Tchebycheff polynomials is required to obtain the flow properties. Numerical differentiation is carried out by means of spline functions. The programme has been used and verified under a wide variety of flows past circular and elliptic cones, tangent ogives and a delta wing body. After a series of numerical experiments it was found that accurate solutions could be found using a 7 × 7 grid, and that the essence of the solution is preserved using a very coarse mesh of 4 × 4. Furthermore, the good agreement obtained with experimental results indicates that it could be applied successfully to problems of practical interest.

Type
Research Article
Information
Aeronautical Quarterly , Volume 27 , Issue 1 , February 1976 , pp. 75 - 86
Copyright
Copyright © Royal Aeronautical Society. 1976

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References

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