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研究生:郭璟璘
研究生(外文):Kuo, Jiing -Lin
論文名稱:暫態量測於震波風洞之應用
論文名稱(外文):Transient Measurements in Application of Shock Tunnel
指導教授:邵耀華---
指導教授(外文):Y. H. Shaw
學位類別:碩士
校院名稱:國立臺灣大學
系所名稱:應用力學研究所
學門:工程學門
學類:機械工程學類
論文種類:學術論文
論文出版年:1997
畢業學年度:85
語文別:中文
論文頁數:110
中文關鍵詞:極音速流熱傳量測震波風洞
外文關鍵詞:Hypersonic flowheat flux measurementShock tunnel
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本研究建立了溫度與熱通量量測系統並應用於極音速震波風洞之
流場校驗以及模型之表面熱通量量測。我們採用同軸式熱電偶以及薄
膜熱傳計,為測試溫度感測器之反應特性,本研究利用震波管中入射
震波之後的流場性質之瞬間變化來觀察溫度感測器之反應。而在氣熱
問題的實際應用上,本研究採用圓錐柱之飛彈基本外型來研究震波風
洞 Mach 6.8 超音速氣流之模型表面熱通量分佈。
我們所建立的量測及相關校正設備已達所需之水準。而由於感測器在
使用過程中會造成表面材質改變,現場的動態校正相當重要。本研究
所採用的熱電偶其反應時間在流場停滯點約為 左右。在震波風洞噴
嘴流場品質校驗方面,精確控制初始操作條件的前提下,風洞流場
重複性很高,可用測試時間約有9.5 ms。自由流馬赫數亦如預期因邊
界層厚度成長而較原噴嘴幾何外型經一維等熵理論預估值小,由實驗
結果( 及 )推估之質流量與動壓歷程為熱傳與力量測之重要參
數。由氣熱問題的量測結果發現模型表面的熱通量集中於停滯點附
近並與Eckert*s參考溫度法理論預估結果接近,顯示由熱電偶量取
溫度歷程配合校正系統及熱傳理論推算熱通量的方式在反應速率及
正確性都有不錯的性能。

In this study, heat-flux measurement system using co-axial
thermocouples and thin film gauges was constructed. Instantaneous
changes of flow properties behind the incident shock in a shock
tube were used to detect the response characteristics of the temperature
sensors. The response time of co-axial gauge at the stagnation point is
about 10msec. Because the surface quality of sensors may change due to
the severe environment in shock tunnel, calibration of sensor on site is
very important. The hypersonic aero-thermodynamic problems on a sharp
cone-cylinder model were studied in which thermal gauges were installed
on the model surface to measure the heat flux. Tests were conducted in
Mach 6.8 flow in a shock tunnel.

The free stream properties in the test section of the shock tunnel were
measured with Pitot probe and stagnation temperature probe. Experimental
results showed good repeatability and accurate control of initial
condition can be achieved. Based on the Pitot pressure results, the useful
test time is about 9.5 ms, and the free stream Mach number is less than
theoretical isentropic value due to the growth of boundary layer thickness.
The mass flux and momentum flux were calculated based on the pitot pressure
and stagnation heat flux (pt2 ,q.sph) via Fay-Riddell relation. The results
of heat flux measurements at the model surface show that the heat flux
concentrates in the vicinity of the stagnation point which agrees well with
the estimation using Eckert*s reference temperature. The measurement and
calibration systems constructed have showed high performance on both accuracy
and frequency response.

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