一组近耦合鸭式布局的低速气动力数值模拟

THE NUMERICAL SIMULATION OF THE LOW SPEED AERODYNAMIC CHARACTERISTICS OF A SET OF CLOSE-COUPLED CANARD CONFIGURATIONS

本文使用位流中前缘离体涡模拟的数值计算方法,对于不可压流动,大迎角情况下的气流流经一组近耦合鸭式布局的流动,进行了数值模拟。分析表明,在大迎角下,在一定的主翼-鸭翼的参数选择和位置配置下,鸭式布局的升力较之单独主翼为高的主要原因是因为鸭翼有推迟主翼离体涡破碎的作用,鸭翼离体涡在主翼翼面上形成的负压以及鸭翼离体涡流动造成的主翼流场的变化,也是提高主翼升力的因素。

By the use of the leading-edge vortex flow simulation method in potential flow, the aerodynamic numerical calculation of a set of closecoupled canard configurations has been conducted, and good agreement between the numerical results and the experimental data was achieved. Analysis shows that under certain main wing and canard positions and geometric parameter selection, owing to the canard effect, the leading-edge vortex breakdown on The main wing is delayed, so that the normal force of the main wing is increased when compared with the canard off case. The suction force on the upper surface of the main wing caused by the canard vortex and the circuit variation of the main wing makes contribution to the normal force on the main wing as well.