Abstract
The computational results presented show good agreement with existing flight test data. A parametric study on the sensitivity of attachment line location and crossflow profiles to alpha was conducted. For the 20 case, the attachment line is very close to the leading edge. However, for a = 0.00 and 3.670, the outboard attachment point moves much further downstream relative to the inboard attachment point. At different angles-of-attack the boundary layer thickness and stream-wise velocity profiles do not change significantly. There is, however, a significant change in the crossflow velocity profiles with different angles-of-attack. The trends exhibited in the crossflow velocity profiles indicate that as the angle of attack is decreased from 3.670 to 0.00, the maximum crossflow velocity at a fixed location increases.
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Flores, J., Holst, T.L., Kaynak, U., and Thomas, S.D., “Transonic Navier-Stokes Wing Solutions Using A Zonal Approach: Part 1. Solution Methodology and Code Validation,” AGARD Paper 30A, April 1986.
Flores, J., Reznick, S.G., Holst, T.L., and Gundy, K., “Navier-Stokes Solutions for a Fighter-Like Configurations,” AlAA Paper 87-0032, Jan. 1987.
Flores, J. and Chaderjian, N.M., “Zonal Navier-Stokes Methodology for Flow Simulation about a Complete Aircraft”, Journal of Aircraft, Vol. 27, No. 7, July 1990, pp.583–590.
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© 1993 Springer-Verlag
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Flores, J. (1993). Effects of angle of attack on the leading edge attachment line. In: Napolitano, M., Sabetta, F. (eds) Thirteenth International Conference on Numerical Methods in Fluid Dynamics. Lecture Notes in Physics, vol 414. Springer, Berlin, Heidelberg. https://doi.org/10.1007/3-540-56394-6_261
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DOI: https://doi.org/10.1007/3-540-56394-6_261
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