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Computational and experimental investigation of a nonslender delta wing


Reference:

Gordnier, R. E., Visbal, M. R., Gursul, I. and Wang, Z., 2009. Computational and experimental investigation of a nonslender delta wing. AIAA Journal, 47 (8), pp. 1811-1825.

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Official URL:

http://dx.doi.org/10.2514/1.37848

Abstract

Computational simulations have been performed for a 50-deg-sweep delta wing with a sharp leading edge at a 15 deg angle of attack and moderate Reynolds numbers of Re 2 105, Re 6:2 105, and Re 2 106. A sixthorder compact-difference scheme with an eighth-order low-pass filter is used to solve the Navier–Stokes equations. Turbulence modeling has been accomplished using an implicit large eddy simulation method that exploits the highorder accuracy of the compact-difference scheme and uses the discriminating higher-order filter to regularize the solution. Computations have been performed on a baseline mesh of 11:3 106 grid points and a refined mesh of 35 106 grid points. An assessment of grid resolution showed that significantly finer-scale features of the flow could be captured on the refined mesh, providing a more accurate representation of the complex, unsteady, separated flow. Comparisons are also made with high-resolution particle image velocimetry images obtained for the two lower Reynolds numbers. The numerical results are examined to provide a description of the mean and instantaneous flow structure over the delta wing, including the separated vortical flow, vortex breakdown, surface flow features, and surface boundary-layer transition near the symmetry plane. The effect of Reynolds number on each of these features is assessed.

Details

Item Type Articles
CreatorsGordnier, R. E., Visbal, M. R., Gursul, I. and Wang, Z.
DOI10.2514/1.37848
DepartmentsFaculty of Engineering & Design > Mechanical Engineering
Research CentresAerospace Engineering Research Centre
RefereedYes
StatusPublished
ID Code15330

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