Hostname: page-component-cb9f654ff-hn9fh Total loading time: 0 Render date: 2025-09-06T06:29:33.202Z Has data issue: false hasContentIssue false
  • English
  • Français

Numerical exploration of starting processin supersonic nozzle

Published online by Cambridge University Press:  03 February 2016

S. Saha  and
D. Chakraborty
S. Saha
Affiliation:
Computational Combustion Dynamics Division, Defence Research and Development Laboratory, Hyderabad, India
D. Chakraborty
Affiliation:
Computational Combustion Dynamics Division, Defence Research and Development Laboratory, Hyderabad, India
Get access Rights & Permissions [Opens in a new window]

Abstract

The starting process in a supersonic nozzle isnumerically simulated. The Navier Stokes equations,in axisymmetric form, are solved using a higherorder spatial and temporal accurate scheme. Goodcomparisons between experimental and numericalvalues of various flow parameters form the basis offurther analysis. The insight of the startingprocess in the nozzle, namely, the movement ofprimary and secondary shocks and contactdiscontinuity, has been obtained through analysis ofvarious flow parameters. It has been observed thatthe inviscid phenomenon is more predominant in theflow development process. Parametric studies havebeen carried out to determine the effect of nozzledivergence angle on the starting process.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1115 , January 2007 , pp. 51 - 58
Copyright
Copyright © Royal Aeronautical Society 2007 

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.)

Article purchase

Temporarily unavailable

References

1. Jacob, P.A., Simulation of transient flow in a shock tunnel and a high mach number nozzle, NASA- CR – 187606, 1991.Google Scholar
2. Stalker, R.J., A study of free-piston shock tunnel, AIAA J, 1967, 5, (12), pp 2160–2165.Google Scholar
3. Hornung, H.G., Performance data of new free-piston shock tunnel at GALCIT, AIAA, 1992, Paper No 92-3943.Google Scholar
4. Itoh, K., Ueda, S., Tanno, H., Komuro, T. and Sato, K., Hypersonic Aerothermodynamics and scramjet research using high enthalpy shock tunnel, Shock Waves, 2002, 12, pp 93–98.Google Scholar
5. Paull, A., Stalker, R.J. and Mee, D.J., Experiments on supersonic combustion ramjet propulsion in a shock tunnel, J Fluid Mechanics, August 1995, 296, pp 159–183.Google Scholar
6. Jialing, L. and Weixiong, L., Recent progress of CARDC in experimental and computational scramjet research, Proceeding of East West High Speed Flow Field Conference (EWHSFF 2005), Beijing, China, pp 24–30.Google Scholar
7. Gaydon, A.G. and Hurle, I.R., The Shock Tube in High Temperature Chemical Physics, Reinhold, New York, USA, 1963.Google Scholar
8. Smith, C.E., The starting process in a hypersonic nozzle, J Fluid Mechanics, 1966, 24, pp 625–640.Google Scholar
9. Amann, H.O. and Reichenbach, H., Unsteady Flow Phenomena in Shock Tube Nozzle, Recent Development in Shock Tube Research, edited by Bushader, D. and Griffith, W. Stanford University Press, Stanford, CA, USA, 1973, pp 96–112.Google Scholar
10. Amann, H.O., Experimental study of the starting process in a reflection nozzle, Physics of Fluids, 1969, 12, (5), pp 150–153.Google Scholar
11. Saito, T., Timofeev, E.V., Sun, M. and Takayama, K., Numerical and experimental study of 2D nozzle starting process, Proceedings of the 22nd International Symposium of Shock Waves, 1999, London, UK, Paper No 4090.Google Scholar
12. Chopra, H.S., Greatrix, D.R. and Kawall, J.G., Transient shock wave interaction with rocket nozzle – cold flow study, 2003, AIAA Paper 2003 – 4669.Google Scholar
13. Prodroumou, P. and Hillier, R., Computation of Unsteady Nozzle Flows, Proceedings of the 18th International Symposium on Shock Waves, 1991, pp 1113–1117.Google Scholar
14. Igra, O., Wang, L., Falcovitz, J. and Amann, O., Simulation of starting flow in a wedge like nozzle, Shock Waves, 1998, 8, pp 235–242.Google Scholar
15. Saito, T. and Takayama, K., Numerical simulation of nozzle starting process, Shock Waves, 1999, 9, pp 73–79.Google Scholar
16. Tokarick-Polsky, S. and Cambier, J.L., Numerical study of transient flow phenomena in shock tunnel, AIAA J, 1994, 32, (5), pp 971–978.Google Scholar
17. Mouronval, A.S., Hadjadi, A.A., Kudryavtsev, A. and Vandromme, D., Numerical investigation of transient nozzle flows, International J Shock Waves, 2002, 12, (5), pp 403–411.Google Scholar
18. Mouronval, A.S. and Hadjadi, A., Numerical study of the starting process in a supersonic nozzle, J Propulsion and Power, 21, (2), 2005, pp 374–378.Google Scholar
19. Kaneko, M. and Nakamura, Y., Numerical investigation of unsteady flow field with shock interaction in a shock tunnel, AIAA paper 2001-0742, 2001.Google Scholar
20. Chen, C.L., Chakravarthy, S.R. and Hung, C.M., Numerical investigation of separated nozzle flows, AIAA J, 32, (9), 1994, pp 1836–1843.Google Scholar
21. Nasuli, F. and Onofri, M., Viscous and inviscid vortex generation during startup of rocket nozzle, AIAA J, May 1998, 36, (5), pp 809–815.Google Scholar
22. Wang, T., Transient Two-Dimensional Analysis of side load in liquid rocket engine nozzle, AIAA Paper 2004 – 3680, 2004.Google Scholar
23. Fluent Version 6.0 User’ guide, Fluent Incorporated, New Hampshire, 2001 Google Scholar
24. Jiang, G. and Shu, C.W., Efficient implementation of weighted essentially non-oscillatory scheme, J Computational Physics, 126, (1), 1996, pp 202–228.Google Scholar