Abstract
Solutions to the problem of steady transonic flow of an inviscid perfect gas past plane lifting airfoils are computed using a time dependent formulation. The steady solution to the system of hyperbolic partial differential equations is obtained as the asymptotic limit of flow for large times. A coordinate system, which makes use of a conformal map of the interior of the unit circle onto the exterior of the airfoil, is used. The conservation laws are expressed in terms of polar coordinates on the interior of the unit disc and are solved using a second order accurate method. To extend the numerical solution to the boundary of the unit disc the method of characteristics is used.
This research was supported under AEC Contract No. AT(11-1)-3077
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References
Kacprzynski, J. J., Ohman, L. H., Garabedian, P. R. and Korn, D. G., NRC of Canada Aeronautical Report LR-554, Ottawa, 1971.
Bauer, F., Garabedian, P., and Korn, D., Lecture Notes in Economics and Mathematical Systems, Springer-Verlag, 1972.
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© 1975 Springer-Verlag
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Mirin, A.A., Burstein, S.Z. (1975). Difference methods for transonic flows about airfoils. In: Richtmyer, R.D. (eds) Proceedings of the Fourth International Conference on Numerical Methods in Fluid Dynamics. Lecture Notes in Physics, vol 35. Springer, Berlin, Heidelberg. https://doi.org/10.1007/BFb0019763
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DOI: https://doi.org/10.1007/BFb0019763
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