亚音速飞行器壁面沟槽减阻研究与应用

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%。

Riblet surface drag reduction on subsonic aircraft

Strong shearing at the solid-vapor interface is the main cause of wall skin friction on subsonic aircraft.The k-ε turbulence model was used to study the characteristics of the microvortexes in the riblet grooves and to analyze the force on the riblet surface caused by the pressure drag.The skin friction coefficient is calculated and the riblet geometry is optimized to obtain the best groove morphology for subsonic aircraft to maximize the drag reduction.Wind tunnel tests show that the riblet surface structure significantly reduces the skin friction for subsonic flight.The skin friction force is reduced from 1.668 N to 0.908 N at 0.4 Ma for a drag reduction of 45.57%.The drag reduction is 13.5% at 0.8 Ma with 18.4% possible at 0.9 Ma.