Abstract
A new computational methodology is presented in this paper for the prediction of the skin friction coefficient for high -speed turbul ent boundary layers with ablation. The method considers the coupled effects of roughness and blowing on skin friction. For the roughness correlation, an implicit formula has been developed based on the roughness correlation for adiabatic 1 and cooling walls . 2 With the critical roughness Reynolds number included, the new correlation successfully models the roughness -augmented skin friction for high -speed flows with Mach number up to 12. For the effects of blowing, the correlation of Lees 3 is used. The method calculates the roughness correlation first and the blowing correlation is made based on the calculated roughness correction. The proposed formulation of the method is universal and can be applied to flat plate or cone geometries. Results presented for the supersonic boundary layer over a flat plate with a wide range of blowing agree well with the experimental data.
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