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Calculation of Potential Flow about Arbitrary Three Dimensional Wings using Internal Singularity Distributions

Published online by Cambridge University Press:  07 June 2016

N. Singh ,
G. Bandyopadhyay  and
B.C. Basu
N. Singh
Affiliation:
Indian Institute of Technology, Kharagpur
G. Bandyopadhyay
Affiliation:
Indian Institute of Technology, Kharagpur
B.C. Basu
Affiliation:
Indian Institute of Technology, Kharagpur
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Summary

A first order panel method has been developed for calculating the incompressible potential flow about arbitrary three-dimensional wings. The method utilises a distribution of source and vorticity singularities on the mean camber surface of the wing and solves for the distribution by satisfying the boundary condition of zero normal flow at selected points on the surface of the wing. The method takes less computing time compared to other existing first order methods for the comparable numerical accuracy. This method can handle wings having cusped trailing edges and thin sections.

Type
Research Article
Information
Aeronautical Quarterly , Volume 34 , Issue 3 , August 1983 , pp. 197 - 211
Copyright
Copyright © Royal Aeronautical Society. 1983

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References

1 Hess, J.L. and Smith, A.M.O. Calculation of potential flow about arbitrary bodies. Progress in Aeronautical Sciences, Vol. 8, Pergamon Press, New York, pp 1-138, 1966 Google Scholar
2 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, January 1972 Google Scholar
3 Hess, J.L. Calculation of potential flow about arbitrary three-dimensional lifting bodies. Final Technical Report. McDonnell Douglas Report No. MOC J5679-01, October 1972 Google Scholar
4 Maskew, B. Calculation of the three-dimensional potential flow around lifting nonplanar wings and wing-bodies using a surface distribution of quadrilateral vortex rings. Department of Transport Technology, Loughborough University of Technology, TT7009, 1970 Google Scholar
5 Kraus, W. and Sacher, P. Das MBB - Unterschall - Panel - Verfahren: Dreidimensionale Potentialtheorie bie beliebig Vorgegebener Mehrkorperanordnung, Masserschmitt - Bolkow - Blohm GMBH, MBB - Bericht NR. UFE 672-70(0), Munchen, Germany, December 1970 Google Scholar
6 Labrujere, Th. E., Loeve, W. and Slooff, J.W. An approximate method for the calculation of the pressure distribution on wing-body combinations at subcriticai speeds. AGARD Conf. Proc. No. 71, September 1970 Google Scholar
7 Woodward, F.A. Analysis and design of wing-body combinations at subsonic and supersonic speeds. Journal ofAivaraft, Vol. 5, No. 6, pp 528-534, December 1968 Google Scholar
8 Morino, L. and Kuo, C.C. Subsonic potential aerodynamics for complex configurations: a general theory. AIAA Journal, Vol. 2, No. 2, pp 191-197, February 1974 CrossRefGoogle Scholar
9 Sells, C.C.L. Iterative method for thick cambered wings in subcriticai flow. A.R.C. RSM No. 3786, 1974 Google Scholar
10 Hunt, B. The panel method for subsonic aerodynamic flows; a survey of mathematical formulations and numerical models and an outline of the new British Aerospace scheme. V.K.I. Lecture Series 1978-4, March 1978 Google Scholar
11 Johnson, F.T. A general panel method for the analysis and design of arbitrary configurations in incompressible flows. NASA Contractor Report 3079, 1980 Google Scholar
12 Bristow, D.R. Development of panel methods for subsonic analysis and design, NASA Contractor Report 3234, 1980 Google Scholar
13 Hess, J.L. Higher-order numerical solution of the integral equation for the two-dimensional Neumann problem. Computer Methods in Applied Mechanics Engineering, Vol. 2, No. 1, February 1973 Google Scholar
14 Johnson, F.T. and Rubbert, P.E. Advanced panel-type influence coefficient method applied to subsonic flows. AIAA Paper No. 75-50, January 1975 Google Scholar
15 Roberts, A. and Rundle, K. Comparison of incompressible flow about bodies and-thick, wings using the Spline Mode system. BAC (CAD) Report Aero MA19, 1972 Google Scholar
16 Basu, B.C. A mean camberline singularity method for two-dimensional steady and oscillatory aerofoils and control surfaces in inviseid incompressible flow. A.R.C. C.P. No. 1391, 1978 Google Scholar
17 Sytsma, H.S., Hewit, B.L. and Rubbert, P.E. A comparison of panel methods for subsonic flow computation, AGARD - AG - 241, May 21, 1971 Google Scholar
18 Butter, D. Private communicationGoogle Scholar