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固/气界面间强烈的剪切作用是亚音速飞行器壁面摩擦阻力产生的主要原因。该文基于k-ε湍流模型及动态网格划分技术,研究沟槽内微漩涡流动特性、沟槽结构对表面受力影响及沟槽内局部压力场及压差阻力的产生原因;以壁面阻力系数为计算目标,对沟槽形貌构型优化,获取亚音速飞行时具有最佳减阻效果的壁面沟槽形貌构型参数。在中国航天某研究院FD06风洞进行试验,试验结果表明:亚音速飞行器壁面沟槽结构可显著降低壁面阻力系数。Ma=0.4时,壁面摩擦阻力由1.7N降低为0.908N,减阻率为45.57%;Ma=0.8时,减阻率为13.5%;Ma=0.9时,减阻率为18.4%。
The strong shearing effect between the solid / gas interfaces is the main reason for the frictional resistance of subsonic aircraft. Based on the k-ε turbulence model and the dynamic meshing technique, the micro vortex flow characteristics in the trench, the influence of the trench structure on the surface and the local pressure field and pressure drop resistance in the trench are studied. The coefficient is the calculation target, and the shape of the groove topography is optimized to obtain the wall groove topography configuration parameter with the best drag reduction effect in subsonic flight. The test was carried out on the FD06 wind tunnel of a China Aerospace Academy. The test results show that the subsurface slot structure of subsonic aircraft can significantly reduce the wall drag coefficient. When Ma = 0.4, the frictional resistance decreases from 1.7N to 0.908N, and the drag reduction is 45.57%. When Ma = 0.8, the drag reduction is 13.5%. When Ma = 0.9, the drag reduction is 18.4%.