Abstract
本文主要是有關於壓力修正法在可壓縮流上的應用，在數值方法上主要根據有限容積法及交錯網格系統，壓力場方面則採用 SIMPLE 法則，本方法的主要特點在於方程式中變數以解每單位體積的量，如ρｕ，ρｖ等，而非一般不可壓縮流中之主要變數ｕ，ｖ等。另外，在超音速區域中為符合其雙曲線(Hyperbolic)的特性，在這裡我們引進了一為依賴馬赫數的監視方程式所控制 retarded pressure 之觀念。在檢視本數值方法之預測能力上，我們將其應用於幾種不同之無黏滯性及紊流之穿音速流場。其中，包括有不同震波強度之準一維噴嘴流， 無黏滯性帶有凸型物(bump)之渠道流及在凸型物後端部份有震波所引起之分離流等，在有關無黏滯流的計算結果中，我們發現本數值方法具有良好之震波截取能力，除了由於引入過多的人為耗散 (artificial dissipation)而在震波附近造成輕微抹平的現象。而在紊流的計算方面採用了三種均基於漩渦黏滯性 (eddyviscosity)假設之紊流模式來計算震波及邊界層之交互作用，從結果顯示，我們得一暫時性之假設，即高雷諾數所預測之結果與實驗值有較佳之吻合性。本文分五章：第一章文獻回顧；第二章數學方法；第三章無黏滯性流的計算；第四章震波與紊流邊界層之交互作用；第五章結論。The present study is concerned with the application of apressure-velocity sloution strategy for compressible flow. Thescheme is based on a finite-volume approach with a staggeredgrid arrangement, while the pressure field is obtained by theSIMPLE algorithm. The main character of this method is theusage of equations based on the properties per unit volumeinstead of the primative variables, and the hyperbolic naturein the supersonic zone is obtained by the introduction of theretarded pressure approach which is controlled by a Mach-number-dependent monitor function. The predictive capabilities of thenumerical method are presented by applying to several inviscidand turbulent transonic flows, including a quasi-one-dimensional nozzle flow with different strengths of the shock,flows over the bump in the inviscid channel and shock inducedboundary layer separation occuring on the aft portion of thebump. In the computation of the inviscid cases, it is foundthat the present scheme gives a well representation of theshock except for the slightly smearing due to the excessiveintroduction of the artificial dissipation. Regarding turbulentflows computations, three types of the eddy-viscosity basedturbulence models are also used to calculate the shock wave/boundary layer interaction. A tentative conclusion is takenthat the high-Re model seems to have better agreement with theexperiment in both the test cases. There are five chapters inthis text: the chapter 1 is the paper review; the chapter 2 isthe mathematical method; the chapter 3 is the computation forinviscid flow; the chapter 4 is the shock wave/turbulentboundary layer interaction; the chapter 5 is the conclusions.