前掠翼布局中鸭翼气动影响的数值模拟

 采用三维Navier-Stokes方程和剪切应力输运（SST）湍流模型，就鸭翼不同位置和形状对前掠翼鸭式布局气动性能的影响进行数值模拟，并针对风洞试验方法难于分部件研究机翼、鸭翼以及机身各自气动特性的缺点，对布局升阻特性按部件分解研究并分析流动机理。研究结果表明：前掠翼鸭式布局气动性能（特别是在大迎角情况下）与鸭翼位置及其形状紧密相关，高位近距后掠式鸭翼可以与机翼产生更为有利的相互干扰，与无鸭翼布局相比最大升力系数提高约28.3%，最大升阻比提高约15.4%，大大地提高了前掠翼布局的纵向气动性能。该研究结果可为先进前掠翼布局飞机的预研和发展提供一定的理论参考。

Numerical Simulation on Aerodynamic Influence of Canard on Forward-swept Configuration

By applying the numerical methods of the 3D Navier-Stokes equation and the standard shear stress transport(SST) model in this artiele, the effect of different canard positions and geometries on the aerodynamic efficiency of a canard with a forward-swept configuration is simulated. While it is difficult to differentiate the aerodynamic characteristics of the various parts of the wing in a wind tunnel experiment, the lift-drag ratio and the flow mechanism of such a configuration are investigated through assembly analysis. The result shows that the improvement of aerodynamic efficiency of the forward-swept wing, especially at high angles of attack, demonstrates a close relationship with the position and geometry of the a canard. A sweep-back canard with a high position and short distance can produce mutually favorable interference with the wing. Compared with the no-canard layout, the maximal lift coefficient increases by about 28.3% and the maximal lift-drag ratio increases by about 15.4%, which highly improves the longitudinal aerodynamic efficiency of a forward-swept wing. Results of the article can thus provide certain theoretical references for the beforehand research and development of the advanced forward-swept configuration.