A Locally TwoDimensional Numerical Method for Calculating ThreeDimensional Supersonic Flows
Abstract
A finite difference method of calculating steady supersonic flow of an inviscid ideal gas is described for the case in which a boundary condition has to be satisfied at the surface of any given complicated body shape. The supersonic flow equations are formulated in an arbitrary nonorthogonal coordinate system and an operator splitting method is used to construct discrete representations of the equations of motion. Results are presented to demonstrate that the method is capable of capturing shock waves satisfactorily and that it produces results in agreement with other theoretical results. Comparisons between numerical and experimental results for an intake cowl shape, which has a sharp comer and which is representative of a class of complicated body shapes of practical interest, indicates that the method can be relied upon to produce accurate results for complicated body shapes.
 Publication:

Journal of Computational Physics
 Pub Date:
 April 1978
 DOI:
 10.1016/00219991(78)900281
 Bibcode:
 1978JCoPh..27..103W