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Calculation of Subsonic Normal Force and Centre of Pressure Position of Bodies of Revolution Using a Slender Body Theory – Boundary Layer Method

Published online by Cambridge University Press:  07 June 2016

K.D. Thomson
K.D. Thomson*
Affiliation:
Department of Defence, Weapon Systems Research Laboratory, Defence Research Centre Salisbury, South Australia
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Summary

The aim of this paper is to present a method for predicting the aerodynamic characteristics of slender bodies of revolution at small incidence, under flow conditions such that the boundary layer is turbulent. Firstly a panel method based on slender body theory is developed and used to calculate the surface velocity distribution on the body at zero incidence. Secondly this velocity distribution is used in conjunction with an existing boundary layer estimation method to calculate the growth of boundary layer displacement thickness which is added to the body to produce the effective aerodynamic profile. Finally, recourse is again made to slender body theory to calculate the normal force curve slope and centre of pressure position of the effective aerodynamic profile. Comparisons made between predictions and experiment for a number of slender bodies extending from highly boattailed configurations to ogive-cylinders, and covering a large range of boundary layer growth rates, indicate that the method is useful for missile design purposes.

Type
Research Article
Information
Aeronautical Quarterly , Volume 31 , Issue 1 , February 1980 , pp. 1 - 25
Copyright
Copyright © Royal Aeronautical Society. 1980

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