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Mechanism of windward vortex shocks about supersonic slender bodies

Published online by Cambridge University Press:  04 July 2016

S. A. Princet  and
N. Qin
S. A. Princet
Affiliation:
School of Engineering, Cranfield University, Bedford, UK
N. Qin
Affiliation:
School of Engineering, Cranfield University, Bedford, UK
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Abstract

A detailed numerical study has been performed to investigate the origin and mechanism of the formation of windward shocks that have been observed on inclined slender bodies at supersonic speeds inside the bow shock wave around the body. It is shown that the feature is associated with the virtual double cone-like deflection of the supersonic stream by the primary vortices and, as such, can be named the ‘vortex shock’.

Type
Research Article
Information
The Aeronautical Journal , Volume 106 , Issue 1063 , September 2002 , pp. 507 - 519
Copyright
Copyright © Royal Aeronautical Society 2002 

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Footnotes

†

Currently at QinetiQ, Bedford

References

1. Esch, H. Wind tunnel investigations of the appearance of shocks in the windward region of bodies with circular cross section at angle-of-attack, DLR-Forschungsbericht 90-15, 1990.Google Scholar
2. Birch, T.J., Allen, J.M. and Wilcox, F.J. Force, surface pressure and flowfield measurements on slender missile configurations at supersonic speeds, AIAA Paper 2000-4207, August 2000.Google Scholar
3. Sturek, W.B., Frist, D. and Taylor, M. Navier-Stokes predictions of missile body separated flows, 1997, Proceedings of the Seventh International Symposium on Computational Fluid Dynamics, Beijing, 15-19 Sept, 1997, pp 84–90.Google Scholar
4. Sturek, W.B., Birch, T., Lauzon, M., Housh, C., Manter, J., Josyula, E. and Soni, B. The application of CFD to the prediction of missile body vortices, AIAA Paper 97-0637, 1997.Google Scholar
5. Birch, T.J., Wrisdale, I.E. and Prince, S.A. CFD predictions of missile flowfields, AIAA Paper 2000-4211,2000.Google Scholar
6. Birch, T.J., Ludlow, D.K. and Qin, N. Towards an efficient, robust and accurate solver for supersonic viscous flows, 2000, Proceedings of the ICAS 2000 Congress, Sept 2000, pp 242.1-7.Google Scholar
7. Osher, S. and Chakravarthy, S.R. Upwind schemes and boundary conditions with applications to Eulers equations in general coordinates, J Computational Physics, 1983, 50, pp 447–485.Google Scholar
8. Van Leer, B. Upwind-difference methods for aerodynamic problems governed by the Euler equations, Led AppI Maths, 1985, 22, pp 327–336.Google Scholar
9. Anderson, W.K., Thomas, J.L. and Van Leer, B. A comparison of finite volume flux vector splittings for the Euler equations, AIAA J, 1986, 24, (9).Google Scholar
10. Ludlow, D.K. IMPNS Theory Guide, DERA technical report, DERA/MSS/MSFC2/TR010713, Sept 2001.Google Scholar
11. Degani, D. and Schiff, L.B. Computation of turbulent supersonic flows around pointed bodies having crossflow separation, J Comp Phys, 1986, 66, pp 173–196.Google Scholar
12. Qin, N. and Jayatunga, C. Algebraic turbulence modelling for vortical flows around slender bodies, 1998, Paper 20, NATO, RTO MP-5, AVT Symposium on Missile Aerodynamics, Sorrento, May 1998.Google Scholar
13. Prince, S.A. The Aerodynamics of High Speed Aerial Weapons, 1999, PhD thesis, Cranfield College of Aeronautics, September 1999.Google Scholar
14. D’espiney, P., Champigny, P., Baudin, D. and Pilon, J.A. Couche limite autour d’un fuselage de missile en incidence en ecoulement supersonique etude experimentale et calculs Navier-Stokes, 1998, AGARD Symposium on Missile Aerodynamics, Paper 19, May 1998.Google Scholar
15. Qin, N. and Foster, G.W. Computational study of supersonic lateral jet flow interactions, J Spacecraft and Rockets, 1996, 33, (5), pp 651–656.Google Scholar