Calculation of three-dimensional supersonic flow around air intakes in regimes with a detached shock wave

A calculation is presented of the flow around axially-symmetric and close to axially-symmetric bodies with a circular throat and a tapering central body by a supersonic stream of an ideal gas at an angle of attack and regimes with a detached shock wave. The method of solution is based on a treatment...

Full description

Saved in:
Bibliographic Details
Published in:U.S.S.R. computational mathematics and mathematical physics 1986, Vol.26 (6), p.65-75
Main Author: Mileshin, V.I.
Format: Article
Language:English
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:A calculation is presented of the flow around axially-symmetric and close to axially-symmetric bodies with a circular throat and a tapering central body by a supersonic stream of an ideal gas at an angle of attack and regimes with a detached shock wave. The method of solution is based on a treatment of the flow in the coupled meridional half-planes of the cylindrical coordinate system in each of which the problem is solved using the Godunov finite-difference scheme and an approximation of the dependence of the flow functions on the meridional angle by means of trigonometric polynomials. An algorithm is proposed for isolating the three-dimensional shock wave, the surface of which has a particular cleavage line (the line of points of the ternary interaction of the shock waves). The possibilities of the method are demonstrated by means of examples.
ISSN:0041-5553
DOI:10.1016/0041-5553(86)90148-5