宽速域翼尖涡及其与斜激波相互作用  

Wingtip vortex and its interaction with oblique shock wave in wide-speed range

作　　者：马印锴 李祝飞[1] 黄琪 杨基明[1] MA Yinkai;LI Zhufei;HUANG Qi;YANG Jiming(Department of Modern Mechanics,University of Science and Technology of China,Hefei 230026,China)

机构地区：[1]中国科学技术大学近代力学系,合肥230026

出　　处：《航空学报》2023年第7期38-50,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12172354,11772325,11621202)。

摘　　要：针对宽速域飞行器产生的翼尖涡及其与斜激波相互作用问题,采用数值模拟方法,在来流马赫数0.2~6.0范围内,研究了翼尖涡的演化特性,并探讨了斜激波诱导翼尖涡破碎的机理。结果表明,在宽速域范围,翼尖涡的切向速度和环量分布仍然符合低速流动中的自相似关系式;在超声速至高超声速流动中,翼尖涡强度沿流向更快地减弱;当翼尖涡与斜激波相互作用时,涡核处压力越低的翼尖涡更容易破碎,而经典的涡破碎理论难以在宽速域范围内准确预测涡破碎现象;通过引入涡核处的压力亏损效应修正经典理论,大幅提升了预测斜激波诱导翼尖涡破碎的能力。Wingtip vortex generated by a wide-speed range flight vehicle and its interaction with oblique shock wave are numerically investigated in a freestream Mach number range of 0.2-6.0.The evolution characteristics of the wing⁃tip vortex are examined and the mechanism of its breakdown induced by the oblique shock wave are revealed.The re⁃sults show that the tangential velocity and circulation distribution of the wingtip vortex in the wide-speed range still con⁃form to the self-similarity relation in the low-speed flow.In supersonic and hypersonic flow regimes,the intensity of the wingtip vortex decreases more obviously along the flow direction.When the wingtip vortex with a lower pressure at the vortex core interacts with the oblique shock wave,the vortex is easier to break down.However,the existing theories are difficult to accurately predict the vortex breakdown in the wide-speed range.When the classic theory is modified by considering the pressure deficit at the vortex core,the ability to predict the vortex breakdown induced by the oblique shock wave is greatly improved.

关 键 词：宽速域 飞行器 翼尖涡 斜激波 涡破碎 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] O354.5[理学—流体力学]