An experimental program has been conducted to study the flow separation phenomena in a truncated ideal contour rocket nozzle. Tests indicate that the off-design overexpanded nozzle flow was dominated by shock-induced boundary-layer separation that demonstrated fluctuating characteristics. The separation shock fluctuates back and forth, the intensity of which shows a strong dependence on the nozzle contour. Asymmetry in flow separation was also observed at certain pressure ratios. The study was made using schlieren flow visualization and surface pressure measurements.
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Saurabh Verma (2002) studied this question.
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