Investigation of three-dimensional separation at wing/body junctions in supersonic flows

The problem of three-dimensional separation at a wing/body junction has been investigated numerically using a three-dimensional Navier-Stokes code which employs the MacCormack's time split, finite volume technique. An algebraic grid generation technique is used for generating the grid at a wing/body junction. Specific computational results on velocity and pressure distribution in the separated flow region are compared with the experimental results. A parametric study of flow parameters, such as Mach and Reynolds numbers, have been carried out to understand their effect in interaction flowfield. The parametric study indicates dependency of the number of vortices at the junction on Mach number and Reynolds number.