Hostname: page-component-7b7567c8c-7pwfn Total loading time: 0 Render date: 2026-11-12T22:46:11.872Z Has data issue: false hasContentIssue false
  • English
  • Français

A high order boundary element formulation for potential incompressible aerodynamics

Published online by Cambridge University Press:  04 July 2016

M. Gennaretti,
G. Calcagno,
A. Zamboni and
L. Morino
M. Gennaretti
Affiliation:
University of Rome III Rome, Italy
G. Calcagno
Affiliation:
University of Rome III Rome, Italy
A. Zamboni
Affiliation:
University of Rome III Rome, Italy
L. Morino
Affiliation:
University of Rome III Rome, Italy
Get accessRights & Permissions [Opens in a new window]

Abstract

A high order boundary element formulation is presented and applied to the solution of potential, incompressible flows around non-lifting and lifting configurations. The high order numerical algorithm is based on a bicubic interpolation of both geometry and quantities over each element of discretisation of the boundary. Numerical validation of the formulation is performed by studying the aerodynamic solution around fuselages and wings, and making comparisons with existing numerical results.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1014 , April 1998, pp. 211 - 219
Copyright
Copyright © Royal Aeronautical Society 1998 

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.)

Article purchase

Temporarily unavailable

References

1. Sytsma, H.S., Hewitt, B.L. and Rubbert, P.E. A comparison of panel methods for subsonic flow computation, AGARD AG 241, 1979.Google Scholar
2. Margason, R.J., Kjelgaard, S.O., Sellers, W.L., Morris, C.E.K., Walkey, K.B. and Shields, E.W. Subsonic panel methods — a comparison of several production codes, AIAA Paper 85-1280, 1985.Google Scholar
3. Morino, L. A general theory of unsteady compressible potential aerodynamics, NASA CR 2464, 1974.Google Scholar
4. PAN AIR, A computer program for predicting subsonic or supersonic linear potential flows about arbitrary configurations using a higher order panel method (Version 1.0). Vol. I. Theory Document, NASA CR 3251, 1980.Google Scholar
5. Maskew, B. Prediction of subsonic aerodynamic characteristics: a case for low order panel method, JAircr, 1982, 19, (2), pp 157–163.Google Scholar
6. Roberts, A. and Rundle, K. Computation of Incompressible Flow About Bodies and Thick Wings Using the Spline-Mode System, BAC(CAD) Report Aero Ma 19, 1972.Google Scholar
7. Morino, L. and Gennaretti, M. Boundary integral equation methods for aerodynamics, Computational nonlinear mechanics in aerospace engineering, Atluri, S.N. (Ed), AIAA Progress in Aeronautics and Astronautics, 1992, 146, pp 279–321.Google Scholar
8. Morino, L. Boundary integral equations in aerodynamics, Applied Mechanics Reviews, 1993, 46, pp 445–466.Google Scholar
9. Morino, L., Gennaretti, M. and Calcagno, G. A third order BEM for potential aerodynamics, Proceedings of 1ABEM 95 Symposium, Mauna Lani, Hawaii, 1995.Google Scholar
10. Kress, R. Linear integral equations, Applied Mathematical Sciences 82, Springer Verlag, Berlin, Heidelberg, New York, 1989.Google Scholar
11. Chen, G. and Zhou, J. Boundary Element Methods, Academic Press, New York, 1992.Google Scholar
12. Wagner, S. and Zerle, L. Private communication, 1991.Google Scholar
13. Johnson, F.T. and Rubbert, P.E. Advanced panel-type influence coefficient methods applied to subsonic flows, AIAA Paper 75-50, 1975.Google Scholar