本研究使用自製之可撓式熱膜感測器陣列，應用在傾角15°之矩形斜面平板模型(convex corner)以及彈頭細長比(fineness ratio)為2之彈體模型(tangent ogive missile)於穿音速風洞之流場量測，並使用DC與AC兩種不同的訊號放大電路分別量測流場的熱傳以及擾動現象，依據流場在分離位置的熱傳效應最不理想，以及訊號之間相關性係數較低的資訊，找出流場分離位置的訊號特性。
Convex corner模型量測上，配合小波轉換分析找出震波移動現象與下游流場分離之間的關係，發現在馬赫數為0.8的狀況下會有震波形成，而明顯的震波移動會使得分離位置發生頻率範圍在1~2KHz之間的特徵頻率。彈體模型的量測主要藉由熱傳效應的變化以及相鄰感測器之間擾動量的相關性係數觀察分離發生的位置，找出主要分離線以及二次分離線發生的位置。

The experiment was carried out to examine the applications of thermal film sensor arrays on a convex corner model and an tangent ogive missile body with fineness ratio of 2 in transonic wind tunnel. AC and DC amplifier circuits were employed to study the unsteady characteristics of flow separation downstream of the convex corner; and identify the signal properties in the neighborhood of location of separation on the surface of the ogive cylinder, respectively.
Using wavelet transform analysis of the fluctuation signals enabled to find that the unsteady motions of shock wave motion on the convex corner model at Mach number 0.8 would induce 1K~2KHz characteristic frequency near the separation position. On the measurement of the tangent ogive missile body, the observations of the heat transfer efficiency and the correlation of the thermal film signals enabled to identify the separation position. As the heat transfer efficiency and the correlation coefficient would drop significantly around the separation position, one was able to identify the positions of the primary separation and secondary separation on the ogive cylinder model.

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