碩士 / 國立虎尾科技大學 / 航空與電子科技研究所 / 100 / In recent years, the majority of the tests are performed using the facility of the wind tunnel implemented, but it will waste a lot of money and time. With the progress of computers, the use of software to carry out numerical simulation becomes feasible. Computational Fluid Dynamics with the computer calculations can reduce the time required for a large number of results obtained from experiments implemented. Comparing to the previous wind tunnels, the calculation of the numerical simulation can minimize the Budgets.
In this article, the CFD-RC software package will be applied to study the aircraft wing and the release of the missile body (including fuel tanks, stores). Both Euler and Navier-Stokes equations are solved to simulate the separation, and the k-ε model is adopted to account for turbulent effects. The trajectory and angle of rotation of calculated solutions are compared to those of relatively experimental and numerical results. Effects of missiles with/without fins and analysis of parameters are discussed. Missiles are obviously stablized when the fins are installed.
| Identifer | oai:union.ndltd.org:TW/100NYPI5294010 |
| Date | January 2012 |
| Creators | Chen-Chieh Line, 連振傑 |
| Contributors | Shih-Ying Yang, 楊世英 |
| Source Sets | National Digital Library of Theses and Dissertations in Taiwan |
| Language | zh-TW |
| Detected Language | English |
| Type | 學位論文 ; thesis |
| Format | 127 |
Page generated in 0.0104 seconds