改善空氣動力特性為飛行器設計的重點。氣流通過凹槽時產生的複雜流動對於高直徑深度比的凹槽會產生力矩，影響凹槽內部物品的投放。而低直徑深度比的凹槽則會因為剪力層撞擊後壁，造成自體共振，影響凹槽周邊結構的安全。對於圓形凹槽流大多數的研究都在不可壓縮流與超音速，為了對於凹槽流流動有更深的了解，在穿音速下不同的流場條件與幾何影響，也需探討。

本研究進行可壓縮凹槽流的實驗研究，馬赫數為0.64-0.83，紊流邊界層厚度分別為7、4mm，圓形凹槽直徑深度比3.22-43.00。實驗運用壓力螢光感測塗料與動態壓力傳感器量測壓力，分析平均值與擾動量，並運用快速傅立葉，將頻譜與Rossiter方程式做比較。

圓形凹槽流其類型分界與矩形凹槽接近。對於凹槽後緣的壓力梯度與壓力擾動量會因為邊界層厚度與深度比上升而減少，且對於凹槽內部體積越大效果越明顯；凹槽後緣的壓力梯度與壓力擾動量亦會因為直徑深度比上升而增加。其次運用螢光壓力感測塗料時發現開放形凹槽流其內部渦流有彎曲的現象。對於震盪頻率，邊界層厚度與深度比效應不顯著。但些微影響Rossiter方程式的參數值。

This study aims to characterize the effect of incoming boundary layer thickness, diameter, depth and Mach number on a compressible, cylindrical cavity flow. The ratio of cavity diameter and depth, D/h, varies from 3.22 to 43.00 and the ratio of boundary layer thickness to depth, δ/h, varies from 0.42 to 7. The results indicate that variation in the value of δ/h affects the amplitude of peak pressure fluctuations, e.g. a decrease in the value of δ/h resulting in an increase in the amplitude of peak pressure fluctuations. The effect of δ/h is more significant on the mean surface pressure distributions for an open cavity, but not for a transitional or a closed cavity. The static pressure near the rear corner for an open cavity decreases when there is an increase in the value of δ/h and the effect on static pressure near the rear corner and peak pressure fluctuations will be more obviously by increasing the cavity volume. The PSP measurements shows that the vortex inside the open cavity is curved in the cross direction. The effect of δ/h on self-sustained oscillating frequency is minimized and there is a minor effect on empirical constants in the Rossiter equation.

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