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研究生:周欣芸
研究生(外文):Shin -Yun Chou
論文名稱:單噴流及雙噴流於稀薄氣體流場之模擬
論文名稱(外文):Simulation of the Structure of Single- and Twin- jet Under Rarefied Conditions
指導教授:吳宗信吳宗信引用關係
指導教授(外文):Jong-Shinn Wu
學位類別:碩士
校院名稱:國立交通大學
系所名稱:機械工程系
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:2003
畢業學年度:91
語文別:英文
論文頁數:147
中文關鍵詞:稀薄氣體噴流
外文關鍵詞:rarefied gassupersonic jet
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利用三維非結構性調適網格、平行化之直接蒙地卡羅法進行單噴流及雙噴留再稀薄氣體流場模擬。在不同的 Knudsen number 及不同壓力比下觀察噴流的結構變化的超音速噴流流場之模擬。分別計算一個及二個噴口,將氬氣噴向低壓環境的模擬。利用流續流體的假設計算出喉管口的出口流場,並帶入直接蒙地卡羅法來模擬。在這個模擬中,上游的停滯壓力跟下游腔體的壓力比值自50變化至真空。以喉管為基礎的Knudsen number 範圍為0.001~0.1,其流場特徵為近流續流到過渡流。結果顯示流場Knudsen number為0.001時可以清楚的描述出barrel shock及Mach disk shock,隨著Knudsen number的增加而消失而成為可壓縮的膨脹流。而隨著壓力比的增加,Mach disk shock 的位置也向下游推移。
Supersonic jets issuing from a sonic orifice over a wide range of the stagnation
knudsen numbers,from a continuum to a near free molecular condition,and over a wide range of the pressure ratio are simulated by the DSMC method. single and twin jets of argon gas from the orifice(s) into a lower-pressure chamber are considered,
in order to minimize the computational time and reduce CPU load. An adaptive mesh-embedding (h-refinement) scheme using unstructured grid and variable time step scheme in three-dimensional Direct Simulation Monte Carlo method is used. The result reproduces very well the jet structure including the Mach disk and the barrel shock for a near continuum flow condition as well as the jets in the transition regime.
CHAPTER 1 INTRODUCTION 1
1.1 BACKGROUND AND MOTIVATION 1
1.2 LITERATURE SURVEY 2
1.3 OBJECTIVES AND ORGANIZATION OF THE THESIS 10
1.3.1 objectives 10
1.3.2 organization of the thesis 10
CHAPTER 2 NUMERICAL METHOD 11
2.1 DSMC METHOD 11
2.2 PARALLEL DSMC METHOD 12
2.3 MESH ADAPTATION 13
2.4 VARIABLE TIME STEP SCHEME 17
Chapter 3 Results and Discussion 22
3.1 FLOW AND SIMULATION CONDITIONS 22
3.2 SIMULATION RESULTS AND DISCUSSIONS 23
CHAPTER 4 CONCLUSIONS AND FUTURE WORK 39
4.1 CONCLUSIONS 39
4.2 FUTURE WORK 39
RERERENCES 41
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