SYNOPSIS The unsteady boundary layer behind a moving shock wave in a rectangular duct 7.62 cm wide × 5.08 cm high has been studied using a high quality schlieren system. Growth of the boundary layer has been compared with the results of calculations for laminar and turbulent flows. The experimental results indicate that three dimensional effects are present which cause, in some cases, very early transition from laminar to turbulent flow. Agreement with theory is satisfactory only in the case of the weakest shock wave examined although the trends in growth rates generally conform to theoretical predictions.
SYNOPSIS Development of the velocity and temperature of the flow behind a shock wave propagating in atmospheric air in a smooth rectangular duct has been followed by hot wire anemometry. Averaged data were analyzed iteratively to yield the velocity and temperature at several points. Property distributions close to the wave front are non-uniform. Far from the front, the steady velocity profile is approximately the same as for flow in a rectangular duct. The temperature profile develops in a similar manner to the velocity but it is difficult to define the boundary layer edge because the temperature decreases with time.
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