Numerical simulation of the effect of a moving wall on separation of flow past a symmetrical aerofoil

Abstract

This paper applies the numerical simulation technique based on the generalized conservation of circulation (GCC) method to investigate the effects of a leading-edge rotating circular cylinder on the suppression of stall flow past a symmetrical Joukowski aerofoil. The variables investigated were the angle of attack α and the ratio of the surface velocity of the cylinder to freestream velocity, C U. The Reynolds number based on chord length is 1.43 × 10 5. It was found that the separation point on the upper surface of the aerofoil shifts downstream with increasing C U and stall flow can be significantly suppressed even at α up to 30° when C U = 4. The lift coefficient C L increases and the drag coefficient C d decreases with increasing C U and the optimum C L/C d occurs at a = 8°. The maximum C L/C d obtained is about 60 at C U = 4. © IMechE 1998.