三音速風洞操作馬赫數之延展與驗證測試

Extension of Operating Mach Number Range and Verification Tests for a Tri-Sonic Wind Tunnel

10.6124/TAASRC.200512_37(4).10

莊書豪(Shu-Hao Chuang)；徐力行(Lih-Shyng Shyu)

風洞 ； 馬赫數 ； 可變噴嘴 ； 流場均勻度 ； Wind tunnel ； Mach no ； Flexible nozzle ； Flow field uniformity

中國航空太空學會學刊

37卷4期（2005 / 12 / 01）

357 - 364

繁體中文

中山科學研究院航空研究所4呎×4呎（1.22公尺×1.22公尺）三音速風洞爲國內最大之高速風洞，民國72年啟用，風速範圍爲0.3至4倍馬赫數，近年來爲滿足國內武器系統發展之更高風速測試需求，依據氣動力理論及風洞運作經驗，研討尋求解決並完成馬赫數爲5之吹試驗證工作，數據顯示馬赫數之準確度均在0.05範圍內，流場均勻度符合品質要求，並以標準模型完成驗證。配合本次馬赫數之提昇，先行完成風洞相關系統調整，並經風洞功能驗證，馬赫數準確度在誤差範圍內，流場均勻度分佈，由原先最大差量0.064降至0.011。

The 4'*4' Tri-Sonic Wind Tunnel at ASRD/CSIST, starting in 1983, is currently the largest high speed wind tunnel in this country. Its operating range was originally from Mach 0.3 to 4. With the increasing need for tests at higher Mach numbers in the development of high speed weapon systems. By aerodynamics theorem and utilizing the practical operating experience of many years, ASRD successfully found the solution to complete this upgrade program. Other relevant systems adjustment were also executed to support this upgrade program. Testing data from tunnel performance test indicated that the Mach number uncertainty were within the error band, and the maximum flow field uniformity fell from 0.064 to 0.011, proving that a prominent accomplishment was achieved in this upgrade program.