Hostname: page-component-cd9895bd7-dk4vv Total loading time: 0 Render date: 2024-12-29T14:03:42.009Z Has data issue: false hasContentIssue false
  • English
  • Français

The Optimum Size of a Rocket Engine

Published online by Cambridge University Press:  04 July 2016

J. E. P. Dunning
J. E. P. Dunning*
Affiliation:
Rocket Propulsion Establishment, Westcott
Get access Rights & Permissions [Opens in a new window]

Summary:

The paper gives a précis account of studies made at the Rocket Propulsion Establishment of the Ministry of Aviation to determine the relationship between the specific weight and thrust of a liquid bi-propellent rocket engine.

Although the need for a better understanding of basic phenomena is established, the conclusion is reached that, within the selected premises, the minimum specific weight is achieved at a thrust level near 50,000 lb. The difference in specific weight between engines of 200,000 lb. thrust and 50,000 lb. thrust is only about 10 per cent and this is shown to be equivalent to only one per cent in propellent specific impulse. Although small, it is considered significant that a minimum has been established and this fact is used as an argument to justify the use of clusters of engines (generally four) to provide levels of thrust greater than 100,000 lb.

Type
Research Article
Information
The Aeronautical Journal , Volume 64 , Issue 600 , December 1960 , pp. 717 - 742
Copyright
Copyright © Royal Aeronautical Society 1960

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.Parker, W. G. and Ruston, G. C. A. (1959). The merits of utilising high energy propellents. A.G.A.R.D. Combustion and Propulsion Panel Meeting, Paris, June, 1959.Google Scholar
2.Crocco, L. (1956). Considerations on the problem of scaling rocket motors. Selected Combustion Problems, II, 457. Butterworths Scientific Publications, London, 1956.Google Scholar
3.Penner, S. S. (1955). Similarity analysis for chemical reaction and the scaling of liquid fuel rocket engines. Combustion Researches and Reviews, 140. Butterworths Scientific Publications, London, 1955.Google Scholar
4.Ross, C. C. (1956). Scaling of liquid fuel rocket combustion chambers. Selected Combustion Problems, II, 444. Butterworths Scientific Publications, London, 1956.Google Scholar
5.Durham, F. P. (1955). Approximate analysis of rocket nozzle scale and dynamic effects. University of Colorado, Eng. Experiment Station Report No. 5. 1955.Google Scholar
6.Coulter, M. C. (1952). Losses in conical and annular supersonic nozzles, with special reference to the loss due to separation and shock at a badly designed throat. M.O.S. P.D.G.W. Report No. EMR/52/1. Imperial College of Science, J.R.L. Report No. 16. 1952.Google Scholar