Abstract
A new surface velocity metho was developed which provides an improved prediction of the flow field near the surface and the aerodynamic forces on the body. The original surface velocity method produces strong flow normal to the wing and the fuselage. This leads to pronounced error in the leading edge region, and low prediction of drag and overprediction of the lift-to-drag ratio. Application of the method to two heavily used transonic potential flow finite-volume programs, FLO27 and FLO28, are presented to illustrate the improvement.
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References
Caughey, D. A. and Jameson, A., 1979; “Recent Progress in Finite-Volume Calculations for Wing-Fuselage Combinations”, AIAA Paper 79-1513.
Jameson, A. and Caughey, D. A.,1977; “A Finite-Volume Method for Transonic Potential Flow Calculations”, AIAA Paper 77-635.
Dillner, B. and Koper, C., 1979; “The Role of Computational Aerodynamics in Airplane Configuration Development”, AGARD Flight Mechanics Panel Symposium, Munich, Germany.
Hicks, R., 1979; private communication, NASA-Ames.
Holst, T. L., 1979; “A Fast, Conservative Algorithm for Solving the Transonic Full-Potential Equation”, AIAA Paper 79-1456.
Wirz, H. J. and Smolderen, J. J., eds. 1978; Numerical Methods in Fluid Dynamics, Hemisphere Publishing Corporation.
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© 1981 Springer-Verlag
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Chen, Hc. (1981). Improved surface velocity method for transonic finite-volume solutions. In: Reynolds, W.C., MacCormack, R.W. (eds) Seventh International Conference on Numerical Methods in Fluid Dynamics. Lecture Notes in Physics, vol 141. Springer, Berlin, Heidelberg. https://doi.org/10.1007/3-540-10694-4_15
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DOI: https://doi.org/10.1007/3-540-10694-4_15
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