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在不同的迎角范围内,通过求解雷诺平均N-S(Navier-Stokes)方程模拟了雷诺数Re=2.4×105下,鸭翼和机翼前缘后掠角均为50°的近距耦合鸭式布局简化模型的绕流结构,并与该模型的风洞测力和水洞流动显示实验结果进行了比较和验证,分析了鸭翼涡和机翼涡在不同迎角下的演变过程.根据鸭翼的不同作用效果,将迎角范围划分为3个区域,分析了各个迎角范围内的主要作用机制.鸭翼涡与机翼涡的演变和干扰过程虽然极为复杂,但可将其概括为诱导、卷绕和破裂作用.分析结果表明:中大迎角以后鸭翼涡都会对主翼涡产生有利影响,尤其在中大迎角下,卷绕起到了主导作用,鸭翼涡产生的增升效果也最好.
At different angles of attack, the near-coupling cannon model with the Reynolds number Re = 2.4 × 105 and the leading edge sweep angle of the wings of 50 ° was simulated by solving the Navier-Stokes equations. The simplified flow-through structure of the model is simplified and compared with the experimental results of the wind tunnel force and the flow field of the model. The evolution of duck wing and wing vortex at different angles of attack is analyzed. The different roles of the wing and the angle of attack range are divided into three regions and the main mechanism of action in each angle of attack is analyzed.The evolution and disturbance process of duck wing vortex and wing vortex are very complex but can be summarized as Inducing, winding and rupturing.The analysis results show that after the mid-high angle of attack, the canard wing vortex will have a beneficial effect on the main wing vortex, especially in the mid-high angle of attack, the winding has played a leading role in the increase of the wing wing vortex The effect is also the best.