本研究的目標為校驗本研究室建立之下吹式馬赫2連管風洞，風洞應用高壓氣源通過蓄熱式加熱器將空氣加熱至780 K作為實驗所需之高焓氣流，經由穩流段、噴嘴進入測試段(7cm×7cm)。風洞校驗將分成三個部分進行，第一部分為測試流場建壓與建溫時間，實驗結果得出風洞建壓時間約200秒，熱流實驗壓力爬升時間較快，但是氣流溫度爬升至780 K的時間較慢，因此冷、熱流實驗建壓時間大致相同；第二部分使用皮托管進行流場速度分布與均勻度的量測，有別於皮托管在次音速的量測，本研究為避免超音速氣流產生的震波影響量測，將分成量測自由流全壓的全壓管及自由流靜壓的壁面量測孔去計算流場馬赫數。此外為不同實驗需求設計全壓管外型，量測流場截面均勻度設計L-type外型以及量測流動角度的C-type外型，流場截面受可拆式壁面限制，流場截面大小設定為4 cm*4 cm的量測面積。流動角度則量測同一個點在不同角度的全壓，以獲得正對氣流的氣流角度。實驗結果顯示熱流裝設整流板的截面平均馬赫數約1.9±0.02，冷流平均馬赫數為1.88±0.02，最大截面誤差皆在3%內，因此推測截面相當均勻，且熱流的流場馬赫數較冷流高。而從流動角度的結果得出氣流偏移角度約在1-2度左右，推測為流場內馬赫波之影響；第三部分為使用視流紋影法觀測測試段流道內之超音速流場現象。從結果發現流道內有斜震波，經分析推測主要為噴嘴產生之馬赫波，且尚未發現明顯與邊界層交互作用的現象，因此認為流道內現象主要受馬赫波影響且仍為超音速氣流。

This thesis aims to calibrate the In-house designed direct connected-pipe wind tunnel, which is composed of settling chamber, nozzle and test section of 49 square centimeters. This study uses two different shape of pitot tubes to measure the pressure and using flow visualization to obtain various flow field conditions. Since the blunt object in the supersonic airflow will produce a bow shock at its front to affect the measured pressure, so this thesis study uses the total pressure after the shock wave measured by the pitot tube and the static pressure at the wall surface to calculate the Mach number.
L-type pitot tube measures the uniformity of the flow field cross-section in the wind tunnel and analyze the Mach number distribution of the measured points, from the results that the average Mach number in the cross-sectional measurement range is 1.90. The C-type pitot tube is used to measure the flow angle. It is considered that the air flow is affected by the Mach wave. The visualization of the flow field uses the Schlieren method to observe the shock wave distribution and boundary layer thickness . The experimental analysis results show that the oblique shock wave in the test section is mainly the Mach wave generated by the nozzle, and it has not yet been seen obviously interacted with the boundary layer. Therefore, it is believed that the distribution of the flow field in the Direct Connected-pipe wind tunnel is mainly affected by the Mach wave in the flow field.

參考文獻
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