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Theoretical Pressure Distribution at Zero Lift at Supersonic Speeds for Slender Delta Wings having Fuselages of Circular Cross Section

Published online by Cambridge University Press:  07 June 2016

R. C. Lock
R. C. Lock*
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

A method is developed for calculating the pressure distribution at zero lift for a class of slender configurations consisting of a wing of delta type plan form combined with a body of revolution of the same overall length. Slender-body and slender-wing theory are combined to take into account the interference between the wing and the fuselage. An expression is found for the pressure at a general point on the wing or fuselage, although some numerical integration is still needed. This expression is simplified to obtain algebraic formulae for the pressure at the wing-fuselage junction and along the top of the fuselage. A further simplification is possible when the fuselage radius is small compared with the local wing semi-span. A particular example is considered consisting of a “Newby” wing with a parabolic fuselage; pressure distributions and drag curves are calculated.

Type
Research Article
Information
Aeronautical Quarterly , Volume 12 , Issue 2 , May 1961 , pp. 95 - 130
Copyright
Copyright © Royal Aeronautical Society. 1961

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References

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