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LOPAN - A low-order panel method for subsonic and supersonic flows

Published online by Cambridge University Press:  04 July 2016

T. D. Rubin
T. D. Rubin*
Affiliation:
Aerodynamics Department, Israel Aircraft Industries, Ben-Gurion Airport, Israel
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Abstract

A low-order panel method is presented for the calculation of subsonic or supersonic linear flow about general configurations. The method uses piecewise constant source, doublet and/or vorticity singularities. The internal Dirichlet boundary condition is applied, providing zero perturbation potential inside the configuration. The external Neumann boundary condition may refer to a condition on the outward conormal component of the perturbation velocity (the so-called 'linearised normal mass flux'). However, the program may, if required, proceed to obtain specified conditions on the outward normal component of the perturbation velocity, using an iterative procedure.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 925 , May 1989 , pp. 177 - 182
Copyright
Copyright © Royal Aeronautical Society 1989 

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References

1. SirLamb, H. Hydrodynamics, Dover, New York, 1945, 57.Google Scholar
2. Morino, L. A finite-element formulation for subsonic flows around complex configurations, TR-73-05. Dec. 1973, Department of Aerospace Engineering, Boston University, Boston, Mass.Google Scholar
3. Woodward, F. A. Development of the Triplet Singularity for the Analysis of Wings and Bodies in Supersonic Flow, NASA CR-3466, Sept. 19811981.Google Scholar
4. Woodward, F. A. and Fournasier, L. Investigation of the Triplet Concept Using a Higher Order Supersonic Panel Method, ICAS-84-1.1.1.Google Scholar
5. Coleman, B. A Supersonic Panel Method Based on the Triplet Singularity, Paper presented at the 26th Israel Conference on Aviation and Astronautics, Feb. 1978.Google Scholar
6. Jacobs, A. IAIFLO User's Manual, Engineering Division Document 870333, Israel Aircraft Industry, Ben-Gurion Air port, Israel, Jan. 1987.Google Scholar
7. Ehlers, F. E., Epton, M. A., Johnson, F. T., Magnus, A. E., and Rubbert, P. E. An Improved Higher-Order Panel Method for Linearized Supersonic Flow, AIAA Paper 78-15, Jan. 1978.Google Scholar
8. Moran, J. and Tinoco, E. N. User's Manual - Subsonic/ Supersonic Advanced Panel Pilot Code, NASA CR-152047, Feb. 1978.Google Scholar
9. Magnus, A. E. and Epton, M. A. PANAIR - A Computer Program for Predicting Subsonic or Supersonic Linear Potential Flows About Arbitrary Configurations Using a Higher Order Panel Method, Vol. I, Theory Document. NASA CR-3251, 1980.Google Scholar
10. Maskew, B. Prediction of Subsonic Aerodynanics - A Case for Low-Order Panel Methods, AIAA Paper No. 81-0252, Jan. 1981.Google Scholar
11. Youngren, H. H., Bouchard, E. E., Coopersmith, R. M. and Miranda, L. R. Comparison of Panel Method Formulations and Its Influence on the Development of QUADPAN, an Advanced Low Order Method, AIAA-83-1827, July 1983.Google Scholar
12. Cenko, A. PANAIR Applications to Complex Configurations, AIAA-83-0007. Jan. 1983.Google Scholar
13. Heaslet, M. A., Lomax, L. and Jones, A. L. Volterra's Solution of the Wave Equation as Applied to Three- Dimensional Supersonic Airfoil Problems, NACA Report 889, Apr. 1947.Google Scholar
14. Woodward, F. A., Tinoco, E. N. and Larsen, J. W. Analysis and Design of Supersonic Wing-Body Combinations, Including Flow Properties in the Near Field, Part I - Theory and Application, NASA CR-73106, Aug. 1967.Google Scholar
15. Carmichael, R. L. and Erikson, L. L. PANAIR - A Higher Order Panel Method for Predicting Subsonic or Supersonic Linear Potential Flows About Arbitrary Configurations, AIAA-81-1255, June 1981.Google Scholar