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 alpha and the ratio of the surface velocity of the cylinder to freestream velocity, CU. The Reynolds number based on chord length is 1.43 x 105. It was found that the separation point on the upper surface of the aerofoil shifts downstream with increasing CU and stall flow can be significantly suppressed even at alpha up to 30 degree when CU = 4. The lift coefficient CL increases and the drag coefficient Cd decreases with increasing CU and the optimum CL/Cd occurs at alpha = 8 degree. The maximum CL/Cd obtained is about 60 at CU = 4.
Numerical simulation of the effect of a moving wall on separation of flow past a symmetrical aerofoil
1998
9 Seiten, 19 Quellen
Aufsatz (Zeitschrift)
Englisch
NUMERICAL CONTINUATION FOR TURBULENT FLOWS PAST AN AEROFOIL
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