臺灣博碩士論文加值系統

本文利用數值模擬，對一反射型震波風洞進行全域的流場模擬，探討整個吹試過程間所發生的暫態流場機制，從第一道隔板破裂開始至吹試過程結束，完整的呈現此期間所發生的暫態流場現象，包含了反射模式發生前的流場特徵，反射震波與接觸不連續面的波交互作用、反射震波/邊界層交互作用引起的震波分叉與壁面噴流現象，以及起始過程中所發生的震波反射、二次震波與分離流等等的現象，最後在測試區中加入一圓球模型，估算其從穩定設立時間開始到結束的暫態流場變化。
統御方程式為三維依時性那維爾-史托克方程式，加入混合成份方程式（驅動段：氦氣、被驅動段：空氣）求解，並以熱力性質多項式修正比熱比，以考量高溫引起的真實氣體效應。數值方法為有限體積法、算則採用顯式上風法及TVD法，為增進計算效率，計算域網格採適形、多區塊，特別在噴嘴附近的格點製作，以多層網格綴接的方式製作。程式驗證以Amann二維噴嘴實驗的模擬，驗證本程式具良好之準確性。此外，研究三種不同模式之比熱比的差異性，並改變第二道隔板的強度、調整噴嘴半角的角度對流場的影響。
本文最終的目的是想藉全域流場的模擬，了解影響風洞吹試的流場機制，提供實驗者在針對風洞吹試前之先期準備及改進實驗程序，減少風洞吹試的花費。

The aim of this thesis is to develop a CFD solver used to simulate the transient flow phenomena in a reflected shock tunnel. These transient flow phenomena include the wave interaction of reflected shock and contact discontinuity, the reflected shock/boundary layer interaction and the starting process of nozzle flow that can affect the duration of test flow in actual conditions. In addition, the flow establishment time of a sphere model in the test section is calculated in this model.
To numerically simulate these transient flow features, a full-size, axisymmetric reflected shock tunnel model is used. The governing equations are the full Navier-Stokes equations, a species equation and a simplified polynomial correlation to simulate the real gas effects. The numerical code has been developed based on the finite volume method coupled with the upwind Roe’s scheme and the total variation diminishing (TVD) method. To increase the calculation efficiency, a multi-block and multi-mesh grid generation techniques are employed in a huge computational domain. The validation of the present code is done to compare with the Amann’s experiment data with a good agreement. By the way, the strength of the secondary diaphragm, the half nozzle angle effect and the difference of the viscous, frozen and equilibrium flows have simulated in this work.
The present computational results have not only confirmed the theoretical characteristics of a shock tube, but also qualitatively presented the phenomena of the transient flow features. This numerical code is a useful tool to demonstrate the actual flow phenomena and to assist the design of experiments.

封面
致謝
摘要
ABSTRACT
目錄
圖錄
符號與縮寫
1.緒論
2.研究內容
2.1反射型震波風洞原理說明
2.2真實氣體效應
2.3實驗暫態流場現象
2.3.1反射震波/邊界層交互作用
2.3.2噴嘴暫態流場
2.4文獻回顧
2.5研究重點
3.問題描述
4研究方法
4.1統禦方程式
4.2數值方法
5結果與討論
5.1各式驗證
5.2反射模式發生前之震波管流場驗證
5.3三種不同模式比熱比的比較
5.4震波管段波交互作用的探討
5.5反射震波/邊界層交互作用之數值模擬
5.6噴嘴起始過程之暫態模擬
5.7風洞測試時間之起迄估算
5.8第二道隔板強度改變對流場的影響
6結論
參考文獻
論文發表
自傳

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