高超声速边界层转捩对旋转钝锥自由飞运动的影响

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)。

Effect of boundary layer transition on free flight motion of hypersonic spinning blunt cone

This paper firstly researchs the free flight motional and aerodynamic characteristics which is affected by boundary layer transition for the hypersonic spinning blunt cone by artificially fixing tripped thread that can produce the change of lami-nar to turbulent on the blunt cone model surface by the wind tunnel free flight test which the motion freedom is not limited ,then gives a contrary analysis with the natural transitional wind tunnel free flight test result .The experiment Mach number is 5 .0 and the free flow Reynolds number based on the model length is 1 .68 × 106 .The experimental result shows that the spinning blunt cone model with artificial tripped thread has an incentive stable flow that result in a dynamic stable free flight motion which the dynamic stability derivative coefficient less than 0;however ,the flow is unstable for the spinning blunt cone model without tripped thread which have a different motion and aerodynamic characteristics and the dynamic stability derivative co-efficient is above zero which lead to the hypersonic blunt cone free flight motion is unsteady .