Hostname: page-component-cd9895bd7-lnqnp Total loading time: 0 Render date: 2025-01-03T16:12:06.278Z Has data issue: false hasContentIssue false
  • English
  • Français

Incipient separation boundary: confirmation of an empirical criterion by Navier-Stokes solutions

Published online by Cambridge University Press:  04 July 2016

N. Qin
N. Qin*
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, Bedfordshire, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

A non-linear methodology based on high resolution Navier-Stokes solutions has been proposed to predict incipient separation boundaries. Comparison has been made between the prediction and an empirical criterion based on vast experimental data.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 999 , November 1996 , pp. 381 - 384
Copyright
Copyright © Royal Aeronautical Society 1996 

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. Needham, D.A. and Stollery, J.L. Hypersonic studies of incipient separation and separated Flows, AGARD CP-4, Separated Flows, Part I, 1966, pp 89–120.Google Scholar
2. Holden, M.S. Theoretical and experimental studies of separated flows induced by shock-wave-boundary-layer-interaction, AGARD CP-4, Separated Flows, Part I, 1966, pp 147–180.Google Scholar
3. Needham, D.A. A heat-transfer criterion for the detection of incipient separation in hypersonic flow, AIAA J, 1965, 3, (4), pp 781–783.Google Scholar
4. Hankey, W.L. Prediction of incipient separation in shock-boundary-layer interactions, AIAA J, 1967, 5, (2), pp 355–356.Google Scholar
5. Inger, G.R. Scaling of incipient separation in high speed laminar flows, Aeronaut J, June/July 1994, 98, (976), pp 227–231.Google Scholar
6. Rudy, D.H., Thomas, J.L., Gnoffo, P.A. and Chakravarthy, S.R.A validation study of four Navier-Stokes codes for high-speed flows, AIAA Paper 89-1838.Google Scholar
7. Qin, N. and Richards, B.E. Finite volume 3DNS and PNS solutions of hypersonic viscous flow around a delta wing using Osher's flux differencing splitting, Proceedings of Workshop on Hypersonic Flows for Reentry Problems II, Springer-Verlag, 1992, pp 947–959.Google Scholar
8. Qin, N., A comparative study of two upwind schemes as applied to Navier-Stokes solutions for resolving boundary layers in hypersonic viscous flow, G.U. Aero Report 9120, Department of Aerospace Science, University of Glasgow, 1991.Google Scholar