轻型无人直升机部件气动特性CFD计算方法研究

Research on CFD Calaulation Method for Aerodynamic Characteristics of Light Unmanned Helicopter Components

桨毂、起落架、平尾和垂尾等部件对直升机的气动特性、稳定性和操纵性等有比较大的影响,因此获得这些部件的气动特性在直升机研制过程中非常重要。分别采用风洞试验和两种CFD计算方法获得了某无人直升机算例样机的桨毂、起落架、平尾和垂尾四个部件的气动特性,并对三种方法得到的结果进行了对比分析。结果表明部件阻力、侧向力和滚转力矩的风洞试验值与CFD计算取值相差比较大,但是三种方法得到的升力、俯仰力矩和偏航力矩值相差比较小。两种CFD方法计算得到的部件气动特性差别比较小。研究结果可为直升机部件的气动特性风洞试验或数值计算提供一定的参考。

The hub,landing gear,flat tail and vertical tail have a relatively large impact on the aerodynamic characteristics,stability and maneuverability of the helicopter. It is very important to obtain the aerodynamic characteristics of these components in the helicopter design process. The wind tunnel and two CFD calculation methods were used to obtain the the aerodynamic characteristics of hub,landing gear,flat tail and vertical tail of one unmanned helicopter example,then the results obtained by the three methods were compared and analyzed. The results showed that the wind tunnel test value of the drag,lateral force and rolling moment was quite different from the CFD calculation fetch value. However,the lift,pitching moment and yaw moment values obtained by the three methods were relatively small. The difference in aerodynamic characteristics of the components calculated by the two CFD methods was relatively small. The research results could provide a reference for the wind tunnel test or numerical calculation of helicopter components.