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The Supersonic Flow Past a Slender Ducted Body of Revolution with an Annular Intake

Published online by Cambridge University Press:  07 June 2016

G. N. Ward
G. N. Ward*
Affiliation:
Department of Mathematics, The University, Manchester
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Summary

The approximate supersonic flow past a slender ducted body of revolution having an annular intake is determined by using the Heaviside operational calculus applied to the linearised equation for the velocity potential. It is assumed that the external and internal flows are independent. The pressures on the body are integrated to find the drag, lift and moment coefficients of the external forces. The lift and moment coefficients have the same values as for a slender body of revolution without an intake, but the formula for the drag has extra terms given in equations (32) and (56). Under extra assumptions, the lift force due to the internal pressures is estimated. The results are applicable to propulsive ducts working under the specified condition of no “ spill-over “ at the intake.

Type
Research Article
Information
Aeronautical Quarterly , Volume 1 , Issue 4 , February 1950 , pp. 305 - 318
Copyright
Copyright © Royal Aeronautical Society. 1950

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References

1. Lightill, M. J. (1948). Supersonic Flow past Slender Bodies of Revolution, the Slope of Whose Meridian Section is Discontinuous. Quarterly Journal of Mechanics and Applied Mathematics, Vol. 1, No. 1, 1948.Google Scholar
2. Ward, G. N. (1948). The Approximate External and Internal Flow Past a Quasi-cylindrical Tube Moving at Supersonic Speeds. Quarterly Journal of Mechanics and Applied Mathematics, Vol. 1, No. 2, 1948.CrossRefGoogle Scholar