A series of conical and three-dimensional computations have been performed for the swept oblique shock wave/turbulent boundary-layer interaction generated by a 20-deg sharp fin at Mach 4 and Reynolds number Reδ∞ = 2.18 × 105 based on the incoming boundary-layer thickness δ∞. The Reynolds-averaged compressible Navier-Stokes equations are employed with turbulence incorporated using the Baldwin-Lomax and Jones-Launder models. The computed results are basically similar for both turbulence models and display general agreement with experimental data for surface pressure and surface flow direction, although underestimating the size of the primary vortex. The computed three-dimensional flowfield displays quasiconical behavior of the surface pressure, surface flow direction, and flowfield contours of static pressure, density, and Mach number over the extent of the computational domain except for an inception region near the fin leading edge. The streamlines of the computed three-dimensional flowfield are qualitatively conical; however, the computed attachment streamline does not exhibit conical behavior within the computational domain. The surface skin friction is not conical. Most of the features of the quasiconical flowfield model of Settles et al. are observed in the computations, including the λ shock, slip line, primary vortex, expansion region, and high-speed jet impingement. Certain features of the flowfield model are not observed in the computations, namely, a “normal” shock near the attachment line, transonic shocklets in the expansion region, and secondary separation. The absence of these features in the computation is believed to be indirectly attributable to limitations in the turbulence models.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering