用于电控旋翼气弹分析的带襟翼翼型气动力模型

Aerodynamic model of airfoil with flap used for electrical controlled rotor aeroelastic analysis

为满足电控旋翼的气弹分析需要,给出了带襟翼翼型的综合时域非定常气动力模型,该模型可以计及襟翼移轴补偿的影响。之后通过与静态、动态风洞吹风数据的比较,验证了该模型的准确性。相关分析表明该模型在翼型未发生失速前具有良好的静、动态气动力预测能力。

In order to satisfy the calculation need of Electrical Controlled Rotor (ECR, or so-called swashplateless rotor), a synthetic unsteady aerodynamic model in time domain is presented to predict the aerodynamic force and moment of the airfoil with a trailing-edge flap. This model is specially developed for Electrical Controlled Rotor aeroelastic analysis, and can take account of the unsteady effect of flap nose overhang. Comparing the calculation results with the steady and dynamic wind tunnel test data is conducted. It can be concluded that the synthetic model has favorable steady and unsteady aerodynamic prediction ability before stall. And this calculation model can also be useful for the aerodynamic prediction of the smart rotor, which is very similar to ECR in structure.