An unstructured rotating mesh methodology is developed for the flow computation over rotor blades. A two-zone mesh is set up with one rotating zone encompassing the blade and one stationary zone extending to the far stream. The rotating zone rotates rigidly with the blade and slides against the stationary zone. The sliding zonal interface is specially designed to enforce the flux conservation between the two zones. The flow fields of a helicopter blade in hover and in forward flight are computed to demonstrate the applicability of the present method.
|Number of pages||7|
|Journal||Transactions of the Aeronautical and Astronautical Society of the Republic of China|
|Publication status||Published - 1999 Dec|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering