Hostname: page-component-78c5997874-j824f Total loading time: 0 Render date: 2024-11-05T21:18:09.185Z Has data issue: false hasContentIssue false
  • English
  • Français

Note on the Extension of Evvard’s Method to Wings with Subsonic Leading Edges Moving at Supersonic Speeds

Published online by Cambridge University Press:  07 June 2016

G. J. Hancock
G. J. Hancock*
Affiliation:
Queen Mary College, University of London
Get access

Summary

Evvard’s technique is applied to the problem of a thin finite wing moving at a supersonic speed when the leading edge is subsonic. It is developed in two methods:—

  • (i) in which the relationship between the pressure loading and the integrals of the downwash over the wing surface is extended as far as possible, and which has to be computed numerically;

  • (ii) in which approximations are made for the upwash velocities in the neighbourhood of the leading edge, resulting in a series of standard integrals for the estimation of the pressure loading.

Method (ii) is applied to the pressure loading on a flat plate triangular wing and cropped delta wing, and the application to more general shapes is discussed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 8 , Issue 1 , February 1957 , pp. 87 - 102
Copyright
Copyright © Royal Aeronautical Society. 1957

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. Evvard, J. C. Use of Source Distribution for Evaluating Theoretical Aerodynamics of Thin Finite Wings at Supersonic Speeds. N.A.C.A. Report 951, 1950.Google Scholar
2. Robinson, A. Rotary Derivatives of a Delta Wing at Supersonic Speeds. Journal of the Royal Aeronautical Society, Vol. 52, pp. 735–752, November 1948.CrossRefGoogle Scholar
3. Stewartson, K. On Linearized Potential Theory of Unsteady Supersonic Motion. Symposium on Aerodynamics. Institute of Aerophysics. University of Toronto, 1954.Google Scholar
4. Brown, C. E. Theoretical Lift and Drag on Thin Triangular Wings at Supersonic Speeds. N.A.C.A. Report 839, 1946.Google Scholar
5. Cohen, D. M. Formulae for Supersonic Loading, Lift, Drag of Flat Swept-Back Wings with Leading Edges behind Mach Lines. N.A.C.A. T.N. 1050, 1952.Google Scholar
6. Stewart, H. J. and Li, T. Y. Periodic Motions of a Rectangular Wing Moving at Supersonic Speeds. Journal of the Aeronautical Sciences, Vol. 17, pp. 529–539, September 1950.CrossRefGoogle Scholar
7. Stewart, H. J. and Li, T. Y. On an Integral Equation in the Supersonic Oscillating Wing Theory. Journal of the Aeronautical Sciences, Readers Forum, Vol. 20, October 1953.Google Scholar
8. Evvard, J. C. Effects of Yawing Thin Pointed Wings at Supersonic Speeds. N.A.C.A. T.N. 1429, 1947.Google Scholar
9. Etkin, B. and Woodward, F. A. Lift Distribution on Supersonic Wings with Subsonic Leading Edges and Arbitrary Angles of Attack. Proceedings of the Second Canadian Symposium on Aerodynamics. Institute of Aerophysics. University of Toronto, 1954.CrossRefGoogle Scholar