带后缘襟翼翼型的非定常气动特性数值仿真

CFD Simulation of Unsteady Aerodynamics of Airfoil with Trailing-Edge Flap

研究直升飞机性能优化问题,旋翼系统是直升机振动的最主要来源。主动后缘襟翼控制技术可以在源头上抑制直升机的振动,准确预测与分析后缘襟翼-翼型的非定常气动特性是主动后缘襟翼设计的基础。在Fluent计算平台上采用Navier-Stokes方程,分析了在亚音速条件下,后缘襟翼的NACA0012翼型在襟翼与翼型均做俯仰振荡运动时的气动特性,对襟翼的偏角、襟翼与翼型之间的缝隙、以及马赫数等因素对翼型气动特性进行仿真。对结果进行比较,验证了计算的正确性,为后缘襟翼非定常气动力的分析提供了重要的依据。

Helicopter rotor system is the largest source of vibration.Active trailing edge flap control technology can suppress the vibration of the helicopter fundamentally.It is the basis of designing active trailing edge flap-airfoil to forecast accurately and analyse unsteady aerodynamic characteristics of trailing-edge flap.Based on Fluent platform,Navier-Stokes equations is used to perform unsteady aerodynamic analysis of NACA 0012 airfoil with oscillating flap and airfoil in subsonic flow.Results are validated with wind tunnel test data.In addition,the effects of parameters,such as flap angle,gap between flap and airfoil,and Mach number,on flap-airfoil aerodynamics,are also studied to get some conclusions.The conclusions are available for the unsteady aerodynamics analysis of the trailing-edge flap.