流线追踪内转式低音爆进气道的设计方法及流动特征  

Designing Method and Flow Characteristic of Streamline-Traced Inward-Turning Low-Boom Inlet

作　　者：田亚洲 袁化成[1] 张玲玲[2] 宁啸天 刘甫州 TIAN Ya-zhou;YUAN Hua-cheng;ZHANG Ling-ling;NING Xiao-tian;LIU Fu-zhou(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《推进技术》2021年第8期1798-1806,共9页Journal of Propulsion Technology

基　　金：南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20190208)。

摘　　要：为了降低内转式进气道的音爆强度,设计了一种具有曲内收缩前体和零度唇罩角的流线追踪内转式低音爆进气道,采用数值仿真方法初步研究其在不同工况下的流场结构和流动特征。结果表明:由于零度唇罩角,低音爆进气道的唇罩激波微弱,对唇罩外侧的流场影响较小,因此内转式低音爆进气道的音爆显著低于常规内转式进气道,其中在设计马赫数Mad=2.2通流状态下相比下降约94.18%;由于内唇罩面向内偏折,导致唇口反射激波强度增加,总压损失增加,内转式低音爆进气道总压恢复系数略低于常规内转式进气道;内转式低音爆进气道的音爆不但与其唇罩角有关,而且与其飞行工况有关,飞行攻角越大、来流马赫数Ma∞<Mad越小,音爆越大;其中,在攻角α=0°时,其音爆比α=6°时减小约86.69%;在Ma∞=2.2时,其音爆比Ma∞=1.85下减小约91.93%。In order to reduce the sonic boom,a streamline-traced inward-turning low-boom inlet was de⁃signed,which features curved generatrix internal flowfield and zero-angle cowl.The flow field structure and flow characteristics of the inlet under different operating conditions were studied by numerical simulation.The results show that the shock wave is weak and has little effect on the flow field of cowl exterior due to the zero-angle cowl,and the sonic boom of the inward-turning low-boom inlet is significantly lower than that of the conventional in⁃ward-turning inlet,which is about 94.18%lower than that of fully opened state with design Mach number.The re⁃flection shock wave intensity of the inner lip increases due to the cowl internal surface and it results in the in⁃crease of the total pressure loss.Therefore,the total pressure recovery coefficient of the inward-turning low-boom inlet is slightly lower than that of the conventional inward-turning inlet.Except for the angle of attack,the sonic boom of the inward-tuning low-boom inlet is associated with the operating conditions with the larger degree of the angle of attack or the lower freestream Mach number(Ma∞<Mad).The sonic boom of 0°angle of attack is re⁃duced by about 86.69%,compared with the 6°angle of attack.The sonic boom of Ma∞=2.2 is decreased by about 91.93%,compared to Ma∞=1.85.

关 键 词：音爆强度 曲内收缩流场 零度唇罩角 内转式低音爆进气道 流动特征 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]