|
| Numerical simulation on the inviscid flowfield of transonic hovering rotor using implicit method and WENO schemes |
| Received:November 04, 2008 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7511/jslx20104006 |
| KeyWord:rotor hover Euler equations WENO schemes Roe scheme implicit scheme |
| Author | Institution |
| 徐丽 |
上海大学 上海市应用数学和力学研究所,上海;上海电力学院 数理系,上海 |
| 杨爱明 |
复旦大学 力学与工程科学系,上海 |
| 丁珏 |
上海大学 上海市应用数学和力学研究所,上海 |
| 翁培奋 |
上海大学 上海市应用数学和力学研究所,上海 |
|
| Hits: 2110 |
| Download times: 1376 |
| Abstract: |
| The most complex flows in aviation are probably those that occur over rotorcraft. To search one numerical method to exactly predict the rotor wake is an unsolved problem. A high-order upwind scheme is developed to compute the inviscid flow field of a helicopter rotor in hover using implicit finite volume method. Roe Riemann solver which is a high-resolution scheme and a flux-difference splitting scheme is adopted to compute inviscid flux. For better accuracy, 5th order weighted essentially non-oscillatory (WENO) schemes are adopted to interpolate higher order left and right states across a cell interface, and compared with MUSCL schemes. To improve the efficiency and convergence to steady state, the LU-SGS implicit algorithm is used. The performance of the schemes is investigated in a transonic inviscid flow around hovering rotor. The results reveal that WENO-Roe has the great capabilities to capture shock with higher resolution than MUSCL-Roe, which shows the advantage of increasing precision, and the implicit LU-SGS scheme is more efficient than 5th order Runge-Kutta method. |
|
|
|