Computational and experimental investigation of a nonslender delta wing
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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.
|Creators||Gordnier, R. E., Visbal, M. R., Gursul, I. and Wang, Z.|
|Departments||Faculty of Engineering & Design > Mechanical Engineering|
|Research Centres||Aerospace Engineering Research Centre|
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