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通过在钝锥模型表面上布置人工绊线促使边界层强迫转捩,采用运动自由度不受约束的风洞模型自由飞试验技术研究边界层转捩对高超声速旋转钝锥自由飞行运动特性和气动特性的影响规律,并与自然转捩的旋转钝锥风洞模型自由飞试验结果作对比分析,试验马赫数为5.0,以模型长为特征尺寸的自由流雷诺数为1.68×106。研究结果表明:有人工绊线的旋转钝锥在自由飞行过程中有“激励稳定”的绕流流场,产生动态稳定的自由飞运动(动稳定导数系数小于0),而无转捩绊线的旋转钝锥在自由飞行中则有“激励不稳定”的绕流流场,产生动态不稳定的自由飞运动(动稳定导数系数大于0)。
Through the artificial tripwire arranged on the surface of the blunt cone model, the boundary layer is forced to rotate, and the free-flying test of the wind tunnel model with unrestricted freedom of motion is used to study the influence of the boundary layer transition on the free-flying hypersonic rotation and the aerodynamic The results show that the Mach number is 5.0, and the free flow Reynolds number with feature length of model length is 1.68 × 106. The results show that the rotating blunt cone with artificial tripwire has a “stable excitation” flow field during free flight, resulting in a dynamic and stable free-flight movement (dynamic stability derivative coefficient less than 0) without turning The rotating blunt cone of the tripwire has a “motivating instability” flow field in free flight, resulting in a dynamic and unstable free-flight motion (dynamic stability derivative coefficient greater than 0).