UNSTEADY NAVIER- STOKES EQUATIONS COMPUTATION OF MANEUVERING DELTA WINGS ABOUT HIGH MEAN INCIDENCE | ||
International Conference on Aerospace Sciences and Aviation Technology | ||
Article 6, Volume 3, ASAT Conference 4-6 April 1989 , CAIRO, April 1989, Pages 57-71 PDF (3.52 M) | ||
Document Type: Original Article | ||
DOI: 10.21608/asat.1989.25865 | ||
Authors | ||
Osama A. Kandil1; H. A. Chuang2 | ||
1Professor, Department of Mechanical Engineering and Mechanics. Old Dominion University ,Norfolk .VA 23529 USA. | ||
2Assistant professor , Department of Mechanical Engineering and Mechanics, Old Dominion University.Norfolk , VA , 23529 , USA. | ||
Abstract | ||
In this paper, the unsteady three-dimensional thin-layer Navier-Stokes equations in the moving frame of reference are solved by using a time-accurate implicit approximately-factored finite-volume scheme. The steady results for a delta wing of aspect ratio of 1 and 20.5° angle of attack are compared with the experimental data of ref. 18 . With the steay results serving as the initial conditions for the pitching motion the problem is solved. We present comparisons between the Euler equations solution and the thin-layer Navier-Stokes solution for both the steady and unsteady flows. | ||
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