Computational study of incipient leading-edge separation on a supersonic delta wing

A computational study on a 65 deg delta wing at a freestream Mach number of 1.60 has been conducted by obtaining conical Reynolds-averaged, Navier-Stokes solutions on a parametric series of geometries that varied in leading-edge radius and/or circular-arc camber. The computational results showed that increasing leadingedge radius or camber delay the onset of leading-edge separation on the leeside of a delta wing at a specific angle of attack. The Reynolds number was varied from 1 x 106-5 x 10 6 for a turbulent boundary layer and was shown to have a minor effect on the effectiveness of leading-edge radius and/or camber in delaying the onset of leading-edge separation. Both laminar and turbulent boundary-layer models were investigated at a Reynolds number of 1 x 10 6, and the predicted flow pattern was found to change from attached flow for the turbulent boundary-layer model to separated flow for the laminar boundary-layer model.

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