Hostname: page-component-586b7cd67f-r5fsc Total loading time: 0 Render date: 2024-11-25T01:31:28.151Z Has data issue: false hasContentIssue false
  • English
  • Français

The Quasi-Cylinder of Specified Thickness and Shell Loading in Supersonic Flow

Published online by Cambridge University Press:  07 June 2016

H. Portnoy
H. Portnoy*
Affiliation:
Department of Mechanical Engineering, Royal Technical College, Salford
Get access

Summary

The methods of the operational calculus are used to obtain a linear approximation to the shape of the mean camber surface of a quasi-cylinder in a supersonic flow in terms of its shell thickness and loading distributions. The analysis deals with a generalised quasi-cylinder; that is one which, although lying close to a mean cylinder, need not possess axial symmetry. The quasi-cylinder is also permitted to be within the small disturbance field of other separate components, e.g. a centre-body. Because the linearised theory is inadmissable for internal duct flows close to and beyond the first reflected characteristic cone, the present solution is likewise invalid close to and beyond the position where this characteristic meets the mean cylinder. The work given here enables the camber shapes of “ring-wings”, which have been used theoretically to reduce or even nullify the wave-drag of a central slender-body, to be found. An example illustrates the general method.

Type
Research Article
Information
Aeronautical Quarterly , Volume 11 , Issue 4 , November 1960 , pp. 387 - 395
Copyright
Copyright © Royal Aeronautical Society. 1960

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. Lighthill, M. J. Supersonic Flow past Bodies of Revolution. R.& M. 2003, 1945.Google Scholar
2. Ward, G. N. 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, June 1948.Google Scholar
3. Nielsen, J. N. and Pitts, W. C. Wing-Body Interference at Supersonic Speeds with an Application to Combinations with Rectangular Wings. N.A.C.A. Technical Note 2677, 1952.Google Scholar
4. Ward, G. N. Linearized Theory of Steady High-Speed Flow. Cambridge University Press, 1955.Google Scholar
5. Graham, E. W., Beane, B. J. and Licher, R. M. The Drag of Non-Planar Thickness Distributions in Supersonic Flow. The Aeronautical Quarterly, Vol. VI, No. 2, May 1955.Google Scholar
6. Van Der Pol, B. and Bremmer, H. Operational Calculus Based on the Two-Sided Laplace Integral. Second Edition, Cambridge University Press, 1955.Google Scholar
7. Watson, G. N. The Theory of Bessel Functions. Second Edition, Cambridge University Press, 1944.Google Scholar