Numerical investigation of helicopter rotors in ground effect
Numerical investigation of helicopter rotors in ground effect
复制标题
直升机旋翼地面效应数值研究
DOI：
10.2514/6.2012-2913
复制
发表时间：
2012
影响因子：
3.7
通讯作者：
E. Kraemer
中科院分区：
文献类型：
--
作者：
B. Kutz;Ulrich Kowarsch;M. Keßler;E. Kraemer
This study intends to proof the capability of URANS computations to simulate the helicopter flight in the ground effect flow regime. Hover as well as forward flight cases are computed and compared to experimental data. For both flight conditions several parameter variations, such as ground distance, collective pitch and normalized advance ratio, were examined. Overall a good representation of the flow field structure could be obtained, as well as a satisfying approximation for the thrust coefficient. Furthermore, conclusions could be drawn regarding unsteady effects in the wake and their influence on the brown-out phenomenon. Especially the dynamic fluid movement around the Flow Separation Point is a considerable source of unsteadiness and energy introduced in the brown-out particle movement.
