Because of lack of the acceptable data at recirculation region and turbulence model for complex interaction region, it has been difficult to investigate the strong interactive region about an aircraft afterbody. Recently, using nonintrusive way, Amatucci et al. obtained the data about two-stream, supersonic, wake flowfield behind a thick base. This study is adressed to solve numerically the flow field developing a compressible Navier-Stokes code using an implicit numerical algorithm.
Turbulence models used this research are those of k-ω, Sarkar, Baldwin-Lomax and Situ and Schetz. Algebraic models show as good results as Sarkar model. Situ and Schetz model, which consider the compressibility effect at the level of algebraic model, makes little improvement in this case. As it was found for the simple mixing layer, Sarkar's modification for k-ω model underpredicts the spreading rates of both shear layers which are overpredicted by the original k-ω model and it describes the characteristics of the near-wake region satisfactorily.
