Development of a computational model for turbulent boundary layers in order to reduce the friction coefficient in aerodynamic profiles

Abstract

Consulta en la Biblioteca ETSI Industriales (8135)

[eng] Four di erent localized pressure gradient con gurations were computed using a commercially available code by means of four RANS turbulence models (SA, k ¿ , SST and RSM), and compared with experimental measurements of the mean ow quantities and the wall shear stress. The pressure gradients were imposed on a high Reynolds number, 2-D turbulent boundary layer developing on a at plate by changing the ceiling geometry. Two converging humps (at x = 2m and x = 5:5m from the leading edge of the plate) and two diverging humps at the same locations were considered. The SST model provides the best overall predictions for the mean ow quantities when several pressure gradient con gurations are applied. Thus, it appears to be the best current choice when computing mean ow quantities at high Reynolds numbers, and also when the skin friction coe cient has to be estimated accurately.