本研究中吾人應用50度後掠角三角翼與攻角敏感之特性，及五孔皮托管之原理，將三角翼中間挖洞，並利用其中間挖洞部分前、後、左、右四斜面之設計相似於五孔皮托管之設計，藉由五孔皮托管之原理設計一三維風速計。在設計過程中，先藉由模擬軟體FLUENT先做三角翼中間挖洞部份之形狀定義，並觀察其流速及姿態改變與此三角翼中間挖洞部份之斜面關係，並應用FLUENT軟體模擬三角翼中間挖洞斜面與三角翼兩翼緣後端斜面表面之表面剪應力(shear stress)分布情形，並與PIV(Particle Image Velocimetry)實驗結果比較。本研究利用自製之可撓式熱膜感測器陣列，應用於三角翼模型中間挖洞部分四斜面與三角翼兩翼緣後端斜面表面，中間挖洞部分斜面與三角翼兩翼緣後端斜面表面之表面剪應力(shear stress)會隨著攻角以及偏向角的姿態改變而變化，並根據此一物理現象及藉由模擬軟體 FLUENT 之模擬結果來進行此研究。

本實驗風速範圍為3m/s~15m/s，攻角範圍為15°至23°，偏向角範圍為5°至-5°，係應用DC放大電路於低速風洞下，分別量測三角翼中間挖洞斜面與三角翼兩翼緣後端斜面部份之電壓輸出，並觀察其各斜面之電壓輸出值與姿態變化之關係性，以作為三維風速計之姿態判定以及風速量測之依據。

In this investigation, we applied the principle of five holes probe to fabricate a delta-wing model with a middle hole on it. There are four slope surfaces in this middle hole, and it is similar with design of five holes probe. The size of the middle hole was designed by the result of FLUENT simulation. During the process of FLUENTsimulation, we have tried many cases for learning the relationship between velocity, altitude, and shear stress of four slope surfaces of the middle hole. By this simulate way, we have found the design which is sensitive with the velocity and altitude of flying. Also, using this simulate result to compare with the experiment result from PIV(Particle Image Velocimetry), and by this comparison we would like to know it is reliable or not for this investigation. Finally, we found the best design of the middle hole for learning the design which is more reliable to be the model of the three dimensional velocity sensors.

After creating the model which was obtained by the methods described above, we applied MEMS thermal film sensors on the positions which are better for measuring of the velocity and the altitude. Also we tried to do the experiment in low speed wind tunnel. The range of velocity was 3m/s~15m/s, and the angle of attack(α) was researched at the range of 15°~ 23°. Also, the yaw angle(β) was researched at the range of -5°~ 5°.The DC amplifier circuits were employed to process the signals obtained from the four slope surfaces of the middle hole and from the both leading edge of the delta wing. During the experiment, we tried to learn more about the relationship between the output voltage of those sensitive positions and the altitude. However, the velocity and altitude can be determined by the equation which was analyzed from result of the experiment.

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