Theoretical and experimental study of nonadiabatic transonic shock/boundary-layer interaction

Turbulent Transonic Flow Over Smooth and Rough Circular Arc Bumps in a Freestream

“…The sand grain surface roughness heights of the bump surface are discretely increased from 0 (smooth) to 50 m, 580 m, and 1470 m covering the aerodynamically smooth (50 m) to fully rough (580 m and 1470 m) regimes. These particular roughness heights are also used by Inger and Gendt (1997) in their experimental study of transonic flow over a bump in a channel. The roughness is specified on the bump surface only.…”

“…(Fluent, 2006) as well as in (Wilcox, 2002), and hence are not repeated here for brevity. In the earlier studies by Sharif (2005, 2009) (Wilcox, 2002), and the Reynolds stress transport model (RSM) (Launder, Reece and Rodi, 1975), in the computation of turbulent transonic flow over a smooth bump in a channel was evaluated against the experimental data of Liu and Squire (1988) and Inger and Gendt (1997). Some representative comparison of the predictions by different turbulence models against the experimental data of Liu and Squire (1988) is presented in Fig.…”

“…Experiments on the effect of surface roughness on the boundary layer flow have been conducted for rectangular wavy wall channels by Nakagawa and Hanratty (2003). Recent experiments and theoretical study include Inger and Gendt (1997), who experimentally investigated transonic flow over bumps in a channel to study bump surface roughness effects on shock-generated turbulent shock/boundary layer interaction; and roughness study for flat plate at Mach 2.5 by Babinsky, Inger and McConnell (1999), and Babinsky and Inger (2000). These studies found that the effects of roughness on the boundary layer profile prevailed far downstream and thus the effect of surface roughness is not only the increase in boundary layer thickness but also a subsequent increase in the interaction length.…”

Recent investigations of shock wave effects and interactions

“…Holden [34] correlated results from swept interaction heat transfer experiments with the peak surface-pressure ratio, and showed that increased localized heat transfer occurs near the fin and surface intersection. Inger et al [35] investigated the effects of heat transfer on shock/boundary layer interactions for a supercritical airfoil with minimal flow separations and a freestream Mach number of 1.3. It was found that increases in surface temperature of the airfoil led to significant increases in drag and decreases in lift, compared to subcritical airfoil performance with no shock waves present.…”