本研究利用數值模擬方法設計一反射式震波風洞，本風洞主要由一震波管及超音速噴嘴組成，震波管總長度13公尺，驅動段長度3公尺，被驅動段長度10公尺，內徑 18 公分。主要驅動氣體為氦氣，測試氣體為空氣。本設計包含了設計為馬赫數2馬赫及5馬赫的兩組噴嘴，以製造所需馬赫數之測試流場。該風洞將座落在成大歸仁校區航太試驗場。該風洞之主要設計目標為進行馬赫數5以上之極音速外流場以及馬赫數2以上之超音速氫氣燃燒相關實驗。設計標的為風洞出口自由流馬赫數可大於 5，並趨近極音速衝引擎載具之飛行範圍，以符合極音速外流場實驗需求。風洞出口自由流馬數為2時，自由流溫度須超過1300 K絕對溫度， 壓力須大於0.5大氣壓，以符合氫氣在超音速流場中之自燃條件，以利進行超音速氫氣燃燒實驗。反射式震波風洞為一短時間地面測試設備，一般測試時間範圍在毫秒(ms)等級，考量到附屬資料擷取系統能力，本風洞的測試時間需求訂定為至少一毫秒。
本研究利用兩組數值計算程式進行設計參數模擬預估，可壓縮多相流計算程式(Compressible Multiphase Flow Solver, CMFS) 主要用來模擬震波管之操作情形，以獲得溫度，壓力，測試時間等操作參數，UNIC-UNS 主要用來模擬超音速噴嘴之流場狀況。 NASA 的 Glenn Research Center所發展的 Chemical Equilibrium Application (CEA) 程式主要用來驗證CMFS 所模擬之震波管熱力性質，以及計算噴嘴氣源之化學組成。 根據模擬結果，現行設計可以達到符合實驗需求之操作馬赫數，溫度，壓力，以及測試時間。 震波風洞的設計圖面及相關控制系統也將在本論文內一併介紹。

This work aims to report the design of a reflected shock tunnel which will be built and tested at National Cheng Kung University, Taiwan, in year 2010. Notably, this tunnel will be the first ground test facility for hypersonic flow in universities in Taiwan. The design objective of reflected shock tunnel is to produce two free-stream conditions for a preliminary study of scramjet: (1) Mach 2 flow with temperature up to 1300 K and pressure up to 0.5 atm for the design conditions of supersonic Hydrogen combustion and (2) Mach 5 flow for the design condition of external flow. Test time is longer than 1 ms.. This shock tunnel is composed by a 13-meter-long shock tube, of which the diameter is 18 cm. The length of driver section is 3 m and the driven section is 10 m. The preliminary design is based on the numerical simulation results by using two different codes, UNIC-UNS, and a compressible multiphase flow solver (CMFS). In this work, the compressible multiphase flow solver is used to investigate the near-tailored condition and stagnation properties under different initial conditions in helium-air shock tube. The numerical simulations of nozzle flow are implemented by UNIC-UNS. Chemical Equilibrium Application (CEA) code is used to validate the shock tube reservoir conditions simulated by CMFS and calculate the chemical composition of test gas, air, in the reservoir region. According to our simulation results, the present design is satisfactory to meet the required operation conditions. Besides, the schematic diagram and the relevant instrumentation of the reflected shock tunnel are presented in this thesis.

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