### 贴地飞行时直升机旋翼非定常气动特性的CFD分析

1. 南京航空航天大学
• 收稿日期:2015-09-03 修回日期:2015-12-18 出版日期:2015-12-24 发布日期:2015-12-24
• 通讯作者: 招启军
• 基金资助:
国家自然科学基金资助

### CFD Analyses on the Unsteady Aerodynamic Characteristics of Rotor in Forward Flight near the Ground（15-19607）

1, Bo Wang

• Received:2015-09-03 Revised:2015-12-18 Online:2015-12-24 Published:2015-12-24

Abstract: A CFD (computational fluid dynamics) method based on the unstructured grid technique and momentum source method is developed aiming at simulating the unsteady aerodynamic characteristics of a rotor in ground effect (IGE). In this method, the three-dimensional Navier-Stokes equations have been taken as governing equations, the discretization of convective fluxes and the time marching are completed by Jameson scheme and the five-step Runge-Kutta iteration method respectively, and one equation Spalart-Allmaras turbulence model has been em-ployed. The rotor is modeled as a distribution of momentum source, to simulate the ground effect more realistically, the boundary of "moving ground" is used instead of the conventional "stationary ground", and the grids near the rotor plane and between the rotor and the ground are refined to capture the ground vortex more accurate. Consider-ing the motion and control of the rotor under the actual flight environment, the rotor trim is taken into account in the simulation of the rotor flowfield. The aerodynamic forces of trim equations are given by coupling of CFD method and momentum-blade element theory model. In order to improve the robustness and efficiency of the trim method, the genetic algorithm/Quasi Newton hybrid iterative algorithm is proposed and established. Firstly, the method is used to calculate the rotor thrust increment, rotor power required and induced velocity in ground effect. The calcu-lated results are compared with the experimental results aiming at verifying the validity of the method, the problem of ramp increment of rotor power required at a low speed flight have been solved which is difficult for wake analy-sis methods. Then, the flowfields of UH-60A helicopter rotor in different flight heights, different advance ratios have been calculated, the difference of the rotor power required, induced velocity, ground vortex and rotor control are investigated. The calculated results show that the ground vortex appears at small advance ratio, with increase of the advance ratio, it moves along inflow direction in the longitudinal plane and moves close to the ground in axial direc-tion, it becomes weaken continuously and finally disappears.