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General performance reduction equations for reciprocating-engined aircraft with constant-speed propellers

Published online by Cambridge University Press:  07 June 2016

W.J.D. Annand
W.J.D. Annand*
Affiliation:
Rolls-Royce Limited, Hucknall
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Summary

The method of analysis adopted by Cameron has been extended to develop more general equations for the correction of level speed and rate of climb for variation of air temperature and aircraft weight, applicable to aircraft with reciprocating engines of any type driving constant-speed propellers, operating at speeds sufficiently high for compressibility effects on drag and propeller efficiency to be appreciable. Allowance is made in the equations for ram effect on engine power.

The practical application of the equations is discussed, and illustrated by a worked example. The influence of errors in the estimation of the parameters expressing the variation of engine power and propeller efficiency on the corrections, in this particular case, is discussed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 2 , Issue 2 , August 1950 , pp. 111 - 126
Copyright
Copyright © Royal Aeronautical Society. 1950

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References

1. Cameron, D. (1942). British Performance Reduction Methods for Modern Aircraft. A. & A.E.E. Report No. Res/170, 1942 (unpublished).Google Scholar
2. Annand, W.J.D. (1945).The Effects of the Use of Exhaust Thrust on Performance Reduction Methods. A. & A.E.E. Report No. Res/221, May 1945 (unpublished).Google Scholar
3. S.B.A.C. Standard Method of Propeller Performance Estimation (undated).Google Scholar
4. Gardiner, and Mullin, (1949). The Design of Propellers. Journal of the R.Ae.S., Vol. 53, p. 745, August 1949.Google Scholar