A numerical investigation is presented for a two-dimensional shock controlbump (SCB or bump) at transonic speeds. The influence of the bump on drag incomparison to the clean airfoil is evaluated. The numerical procedure is based onReynolds Averaged Navier Stokes (RANS) simulations with several turbulencemodels which are validated by a comparison to known experimental andnumerical results. Parametric study of bump's height and location is presentedand their effect on drag reduction at transonic speeds is assessed. The effect ofthe selected bump on aerodynamic coefficient at off-design conditions is studied.
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