Hostname: page-component-586b7cd67f-rcrh6 Total loading time: 0 Render date: 2024-11-25T07:31:49.240Z Has data issue: false hasContentIssue false
  • English
  • Français

Comparison of Numerical and Experimental “Conical” Flow Fields in Supersonic Corners with Compression and/or Expansion

Published online by Cambridge University Press:  07 June 2016

D A Anderson  and
R K Nangia
D A Anderson
Affiliation:
Iowa State University
R K Nangia
Affiliation:
University of Bristol
Get access

Summary

The flow field produced by the intersection of two plane solid surfaces in a supersonic stream is a complex interference flow. These flows can be fully compressive, fully expansive or of mixed compression-expansion nature. This paper presents a comparison of the flow field structure in an axial corner obtained experimentally with that predicted numerically by using a shock-capturing finite-difference method. The effect of sweep and surface deflection are evaluated and the general influence of each is presented for the three classes of corner flows. The results of this study show that the numerical method is a valuable aid in understanding the flow structure for simple configurations. In addition confidence in the numerical method is gained for use in solving the more general three-dimensional configurations where the flow is non-conical and several wave interactions may be present.

Type
Research Article
Information
Aeronautical Quarterly , Volume 28 , Issue 4 , November 1977 , pp. 293 - 306
Copyright
Copyright © Royal Aeronautical Society. 1977

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Nangia, R K Conical interference structure in supersonic streamwise flows (Secondary title, Wall effect on the front wedge flow field in supersonic intakes). BAC, Filton, AERO/ REP/100, March 1972.Google Scholar
2 Nangia, R K Three-dimensional wave interactions in supersonic intakes. Paper presented at the Second International Symposium on Air Breathing Engines, Sheffield, March 1974.Google Scholar
3 Kutler, P Supersonic flow in the corner formed by two intersecting wedges. AIAA Journal, Vol 12, pp 577-8, May 1974. (Also AIAA Paper 73-675, 1973.)CrossRefGoogle Scholar
4 Shankar, V Anderson, D A Numerical solutions for inviscid supersonic corner flows. Iowa State University, Report ISU-ERI-AMES-74090, Project 101, May 1974.Google Scholar
5 Shankar, V Anderson, D A Kutler, P Numerical solutions for supersonic corner flow. Journal of Computational Physics, Vol 17, pp 160-80, February 1975.CrossRefGoogle Scholar
6 Charwat, A F Redekeopp, L G Supersonic interference flow along the corner of intersecting wedges. AIAA Journal, Vol 5, pp 480-8, March 1967.Google Scholar