空天飞机的边界层转捩

BOUNDARY LAYER TRANSITION FOR AEROSPACE PLANE

本文概述了边界层转捩对空天飞机性能的影响。在介绍确定边界层转捩起始点的线性稳定性理论和简单关联公式之后，又从噪声影响、头部钝头影响和钝锥飞行试验结果等几方面，讨论了线性稳定性理论的应用。接着介绍了采用转捩函数来确定转捩区的方法。从飞行试验、理论计算和风洞试验等三方面，探讨了进一步研究高超声速边界层转捩的途径。重点介绍了ＮＡＳＡＬａｎｇｌｅｙ研究中心的超声速、高超声速静风洞技术的发展。最后，对今后空天飞机边界层转捩的研究工作提出了建议。

The leverage on the performance of aerospace plane from boundary layer transition is presented in outline. The linear stability theory and simple correlations predicated the onset of boundary layer transition arc introduced. The practical application of the linear stability theory is disscussed in some fields, such as the effect of noise,the effect of nose bluntness and the flight testing for blunt cone. The predicating methods of the transition zone employed a transition function are introduced. The route of investigatiug the hypersonic boundary layer transition is probed into from the flight testing, the theoretical computation and the wind tunnel testing. It puts emphasis on the devolopment of supersonic and hypersonic quiet wind tunnels technology at NASA Langley Research Center. Finally, the suggestions of further research works about boundary layer transition for aerospace plane are put for ward.