Hostname: page-component-7b7567c8c-tnzcf Total loading time: 0 Render date: 2026-11-12T05:07:45.983Z Has data issue: false hasContentIssue false
  • English
  • Français

Optimising expansion deflection nozzles for vacuum thrust

Published online by Cambridge University Press:  03 February 2016

N. V. Taylor and
C. M. Hempsell
N. V. Taylor
Affiliation:
University of Bristol, Bristol, UK
C. M. Hempsell
Affiliation:
University of Bristol, Bristol, UK
Rights & Permissions [Opens in a new window]

Abstract

Core share and HTML view are not available for this content. However, as you have access to this content, a full PDF is available via the 'Save PDF' action button.

While expansion deflection (ED) nozzles have traditionally been considered primarily for use as altitude compensating devices to improve the performance of single stage to orbit vehicles, they also offer the potential for enhancing high altitude propulsion systems. If intended to only operate in near vacuum conditions, the complexity of analysis and inherent risks involved in the ED concept are greatly reduced. An integrated approach to the design and performance analysis of such nozzles is presented, comprising a mixture of computational fluid dynamics, the method of characteristics, and a semi-empirical model to allow full analysis of the closed wake flow-field of an ED nozzle. While it is demonstrated that the influence of the parameters used to define the throat region is critical to the successful application of the ED nozzle, it is also shown that with careful design the weight savings possible are significant. The analysis method itself is flexible and rapid, and lends itself well to incremental improvements in accuracy as the flow under consideration becomes better understood.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1088 , October 2004, pp. 515 - 522
Copyright
Copyright © Royal Aeronautical Society 2004 

References

1. Hagemann, G., Immich, H., Nguyen, T.V. and Dumnov, G.E. Advanced rocket nozzles. J Propulion and Power, September 1998, 14, (5), pp 620–634.Google Scholar
2. Mueller, T.J. and Sule, W.P. Annular truncated plug nozzle flow-field and base pressure characteristics. J Spacecraft, November 1973, 10, (11), pp 689–695.Google Scholar
3. Wasko, R.A. Performance of annular plug and expansion-deflection nozzles including external flow effects at transonic mach numbers. Technical Report NASA-TN-D-4462, NASA, April 1968.Google Scholar
4. Rommel, T., Hagemann, G., Schely, C.A., Krulle, G. and Manski, D. Plug nozzle flowfield analysis. J Propulsion and Power, September 1997, 13, (5), pp 629–634.Google Scholar
5. Nasuti, F. and Onofri, M. Theoretical analysis and engineering modelling of flowfields in clustered module plug nozzles. J Propulsion and Power, July-August 1999, 17, (4), pp 544–551.Google Scholar
6. Nasuti, F. and Onofri, M. Analysis of in flight behaviour of truncated plug nozzles. J Propulsion and Power, July-August 2001, 17, (4), pp 809–817.Google Scholar
7. Beichel, R. Nozzle concepts for single stage shuttles. Astronautics and Aeronautics, June 1975, pp 16–27.Google Scholar
8. Mueller, T.J., Sule, W.P. and Hall, C.R. Characteristics of separated flow regions within altitude compensating nozzles. Technical Report NASA-CR-116875, NASA, January 1971.Google Scholar
9. Schorr, C. Constant chamber throttling of an expansoin deflection nozzle. J Spacecraft, July 1970, 7, (7), pp 843–847.Google Scholar
10. Rao, G.V.R. Analysis of a new concept rocket nozzle. J Liquid Rockets and Propellants, 1960, 2:669:682.Google Scholar
11. Taylor, N.V. An Integrated Approach To Expansion Deflection Nozzle Analysis. PhD. Thesis, University of Bristol, 2002.Google Scholar
12. Mayer, E. Analysis of convective heat transfer in rocket nozzles. ARS J, July 1961, 31, (7), pp 911–916.Google Scholar
13. Jameson, A. Transonic aerofoil calculations using the euler equations. In Roe, P.L. (Ed), Numerical Methods in Aeronautical Fluid Dynamics, pp 289–309, 24/28 Oval Road, London, 1982. The Institute of Mathematics and its Applications, Academic Press.Google Scholar
14. Schmidt, W., Jameson, A. and Turkel, E. Numerical solutions of the euler equations by finite volume methods using runge-kutta time stepping schemes. AIAA-Paper No 81–1259, 1981.Google Scholar
15. Kroll, N. and Jain, R.K. Solution of two dimensional euler equations – experience with a finite volume code. Technical Report DFVLR-FB 87–41, DLR, October 1987.Google Scholar
16. Rao, G.V.R. Exhaust nozzle contour for optimum thrust. J Jet Propulsion, June 1958, 28, (6),:377:382.Google Scholar
17. Taylor, N.V. and Hempsell, C.M. Throat flow modelling of expansion deflection nozzles. JBIS, 57(7/8): 242–250, 2004.Google Scholar
18. Taylor, N.V. and Hempsell, C.M. CFD and analytical methods for advanced nozzle calculations, presented as paper IAF-01-S.2.07 at the 2001 IAF conference, Toulouse.Google Scholar
19. Tanner, M. Steady base flows. Progress in Aerospace Sciences, 21: 18–157, 1984.Google Scholar
20. Tanner, M. Two different theoretical approaches to the base pressure problem in two-dimensional flow. Technical Report DFVLF, Germany, May 1978.Google Scholar
21. Mueller, T.J. Determination of the turbulent base pressure in supersonic axisymmetric flow. J Spacecraft, January 1968, 5, (1), pp 101–107.Google Scholar
22. Korst, H.H. A theory for base pressures in transonic and supersonic flow. J Applied Mechanics, December 1956, 23, (4), pp 593–599.Google Scholar
23. Chapman, D.R. An analysis of base pressure at supersonic velocities and comparison wih experiments. Technical Report 1051 NACA, 1951.Google Scholar
24. Tanner, M. Base pressure in supersonic flow; further thoughts on a theoryxs. AIAA J, February 1992, 30, (2), pp 565–566.Google Scholar
25. Cuffel, R.F., Back, L.H. and Massier, P.F. Transonic flowfield in a supersonic nozzle with small throat radius of curvature. AIAA J, July 1969, 7, (7), pp 1364–1366.Google Scholar