Hostname: page-component-586b7cd67f-rcrh6 Total loading time: 0 Render date: 2024-11-25T01:46:28.822Z Has data issue: false hasContentIssue false
  • English
  • Français

A Surface Source and Vorticity Panel Method

Published online by Cambridge University Press:  07 June 2016

J.A.H. Petrie
J.A.H. Petrie*
Affiliation:
(British Aerospace Aerodynamics Department, Kingston-Brough Division and Department of Applied Mathematics, University of Leeds)
Get access

Summary

A panel method for solving potential flow problems of arbitrary geometry is presented. It is very easy to apply and should be very quick to run. Unlike most other panel methods this one does not require a specification of the vorticity distribution in advance, but obtains it as part of the solution. The method is applied to three test cases chosen for their difficult and varied nature.

Type
Research Article
Information
Aeronautical Quarterly , Volume 29 , Issue 4 , November 1978 , pp. 251 - 269
Copyright
Copyright © Royal Aeronautical Society. 1978

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 Hess, J.L. Numerical solution of the integral equation for the Neumann problem with application to aircraft and ships.Google Scholar
2 Lamb, H. Sir Hydrodynamics. Cambridge University Press (1962) 6th edition.Google Scholar
3 Morino, L. and Kuo, C.C. Subsonic potential aerodynamics for complex configurations: a general theory. AIAA Journal, Vol. 12, No. 2, pp 191–197 February 1974.CrossRefGoogle Scholar
4 Rubbert, P.E. and Saaris, G.R. Review and evaluation of a three-dimensional lifting potential flow analysis method for arbitrary configurations. AIAA Paper No. 72–188 (1972).Google Scholar
5 Labrujere, T.E., Loeve, W. and Slooff, J.W. An approximate method for calculation of the pressure distribution on wing-body combinations at subcritical speeds. AGARD CP-11–11 Paper 11 (1970).Google Scholar
6 Hunt, B. and Semple, W.G. Economic improvements to the mathematical model in a plane/constant-strength panel method. Paper presented in brief at the Euromech Colloquium 75. 10–13 May 1976.Google Scholar
7 Hess, J.L. Calculation of potential flow about arbitrary three-dimensional lifting bodies. McDonnell Douglas Co. Dept. No. MDC J5679–01 (1972).Google Scholar
8 Maskew, B. Numerical lifting surface methods for calculating potential flow about wings and wing-bodies of arbitrary geometry. Loughborough University Doctoral Thesis (1972).Google Scholar
9 Maskew, B. A proposal for improving the quadrilateral vortex ring method for application to thick wing/body problems. British Aerospace (Brough) Note No. YAD 3208 (1974).Google Scholar
10 Maskew, B. and Woodward, F.A. Symmetrical model for lifting potential flow analysis. Journal of Aircraft Vol. 13, No. 9 Google Scholar
11 Maskew, B. A subvortex technique for the close approach to a discretized vortex sheet. Paper presented at the Euromech Colloquium 75 10–13 May 1976.Google Scholar
12 Maskew, B. Private communication (1975).Google Scholar
13 Roberts, A. and Rundle, K. Computation of incompressible flow about bodies and thick wings using the spline mode system. B.A.C. (Weybridge) Dep. Aero. MA19 (1972).Google Scholar
14 Jones, A.F. and Grey-Wilson, P.V. The design and definition of a particular three-dimensional swept wing. RAE Tech Memo Aero. 1128 (1969).Google Scholar