抄録
Shock oscillations caused by shock wave / boundary layer interaction in a supersonic nozzle were measured using pressure transducers, schlieren photographs, and Line Image Sensor collimated with schlieren light source. Simultaneous measurements of fluctuating wall pressures and shock images were made to analyze the shock oscillation phenomenon. The shock images oscillating could be successfully captured by Line Image Sensor. The present report aims at adding a knowledge to the previous experiences on shock oscillations, and thereby at better understanding of its mechanism. The present measurements show that the streamwise extent of shock excursion are significantly different from the results of the previous works conducted by the pressure signals alone.
