Numerical analysis of three complex three-dimensional shock wave / turbulent boundary layer interaction flows
Progress in Flight Physics
A set of Reynolds-averaged NavierStokes (RANS) computations with turbulence closure provided by the SpalartAllmaras (SA) model have been carried out for prediction of shock-induced three-dimensional (3D) turbulent separated §ows. The experimental data for di¨erent aerodynamic test con¦gurations have been used for assessing credibility of the numerical method employed. Particularly, shock wave / turbulent boundary layer interactions (SWTBLI) in the vicinity of an asymmetric sharp double-¦n (DF)
... arp double-¦n (DF) with di¨erent (7 • and 11 • ) de §ection angles mounted on a §at plate and two conically sharp cylindrical bodies at varying interbody distances and nose cone angles 60 • and 40 • mounted over a §at plate at freestream Mach number 4, as well as a transonic fan stage operating in the near-stall regime are considered. The gas dynamic structure and topology of 3D separated §ows, surface §ow patterns, and pressure distributions as well as body aerodynamic force prediction are analyzed. A transonic fan stage operating in the near-stall regime and a possibility of applying §ow control is investigated. High Performance Computing was employed to make high resolution computations of these §ows possible, and advanced 3D visualization techniques were employed in order to improve understanding of the separating §ow phenomena.