Experimental and theoretical studies of the shock wave-boundary layer interaction in transonic flows and problems associated with modeling turbulence

ONERA research using laser Doppler velocimetry to characterize shock wave-turbulent boundary layer interactions in transonic flows in order to provide a database from which to define accurate models is discussed. A convergent-divergent (adaptable) wind tunnel is used with a bistable 15 W laser. The experimental runs, covering flows up to Mach 1.3, have demonstrated that the initial shock-boundary layer contact produces large amounts of turbulence due to the arousal of severe longitudinal fluctuations. An approximate method which has proven useful for modeling the shocked boundary layer is described. A sub-domain approach is explored for solving the associated time-averaged Navier-Stokes equations. The technique has not, however, yielded satisfactory matches with experimental data, a discrepancy most pronounced in the region of parietal pressure.