Abstract
This paper is a preliminary work on the numerical study of the near field wake and wingtip vortex behind the juncture of wing and plate. The object is to develop a LES-based code to simulate the near field wake and wingtip vortex, which will help understanding near field wakes and wake control.
The filtered structure function subgrid model was applied on the simulation. The computational approach involves a fully implicit time-marching solver for the Navier-Stokes equation in the generalized curvelinear coordinates with a sixth order compact scheme and an eighth order filter. A one-block high-quality mesh is generated in the complex computation domain. The coordinate transformation metrics are calculated with the high-order compact scheme that is consistent with the flow solver. The parallel computation is accomplished by using domain decomposition and message passing interface (MPI).
The code is validated for simulation of flow transition on a flat plate. The code is also used for simulation of 2-D airfoil vortex shedding. Then the flow field around NACA0014 airfoil is simulated with 8 million grid points. The preliminary results were obtained. To study the near field wake and wingtip vortex behind the juncture of wing and plate, a LES simulation with 25 million grid points is undergoing, in which the angle of attach of the wing is 10°.
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Cai, J., Deng, S., Shan, H., Jiang, L., Liu, C. (2005). LES Investigation of Near Field Wakes Behind Juncture of Wing and Plate. In: Zhang, W., Tong, W., Chen, Z., Glowinski, R. (eds) Current Trends in High Performance Computing and Its Applications. Springer, Berlin, Heidelberg. https://doi.org/10.1007/3-540-27912-1_1
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DOI: https://doi.org/10.1007/3-540-27912-1_1
Publisher Name: Springer, Berlin, Heidelberg
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