Experiments were conducted to observe the cross-sectional structure and streamwise growth of round transverse liquid jets injected into a highly accelerated boundary layer in supersonic flow. The accompanying shock structure was also visualized. In one case, a round jet of acetone was injected into a fully turbulent Mach 2.5 boundary layer that was subsequently accelerated and partially laminarized through a sharp Prandtl-Meyer expansion corner. In the second case, a jet was injected into the laminarized Mach 3.2 boundary layer downstream of the expansion corner at the same jet-to-freestream momentum ratio. The jet and shock structure in both cases were visualized using schlieren optics. Wall-flow patterns were visualized using paints. It was found that the lateral spreading of jets injected downstream of the expansion fan was augmented close to the wall and had a cross-sectional structure significantly different from that of the jet injected upstream: the upstream jet spreads rapidly at the expansion corner in both the lateral and vertical directions. d M P Re St T t p U Nomenclature -diameter of jet orifice -Mach number = pressure = Reynolds number = Stokes number, t p /tf = temperature = time scale for host flow = time scale for the deceleration of acetone droplets = mean velocity = root-mean-square of velocity fluctuations = normal distance from the wall =yU + /v = boundary-layer thickness (y at 0.99£/oo) = displacement thickness = momentum thickness = kinematic viscosity = density = shear stress u ' y y+ d d* 6 v p T Subscripts vd = Van Driest transformed quantity w =wall conditions 0 = stagnation condition oo = freestream conditions
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