الفهرس 
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Abstract
This study deals with the effect of throat aspect ratio On the boundary-layer separation in contoured supersonic wind tunnel nozzles.
Experiments were carried out on a small two-dimensional rectangular wind-tunnel set. The effect of aspect ratio and stagnation pressure on the separation phenomenon was determi¬ned for aspect ratios ranging between 0.536 and 3.81 and for stagnation pressures ranging between 2.2 and 7.6 atmospheres.
The separation mechanism was devited into three main zones, mainly, the separation zone, the expansion zone, and the reattachment zone. It was found that the severity of sep¬aration shocks reaches a maxim= at an aspect ratio of about 2.25. The effect of both aspect ratio and stagnation pressure on the pressure rise during the separation zone, the pressure drop in the expansion zone and the pressure rise during the reattachment zone was investigated.
It was also found that the total length of separated M region, the separation position and the angle of separation shock strongly depend on the aspect ratio.
It was concluded that the separation phenomenon which occurs in contoured nozzle owing to shock waves is strongly dependent upon nozzle aspect ratio and that the change in se¬paration behaviour is attributed to boundary-layer conditions.