隐身进气道地面状态下流场结构  

Flow field structure of stealth inlet under ground state

作　　者：赵庆伟 谢文忠[1] 李腾飞 ZHAO Qingwei;XIE Wenzhong;LI Tengfei(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]北京动力机械研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《航空动力学报》2024年第11期331-342,共12页Journal of Aerospace Power

摘　　要：为探明隐身进气道在地面状态下流场恶劣的原因,分别对三角形和M形等斜切口面进气道在地面状态下的流场结构进行数值仿真分析,并研究了唇口占比和内通道偏距对M形进口进气道地面工作特性的影响规律。结果表明:三角形口面进气道在进口对称面附近形成一个巨大的三维分离涡(一半流场),而M形口面进气道在侧唇口和上唇口交汇处形成一对尺度相对较小的旋涡,而且三角形口面进气道出口畸变指数过大,难以满足进/发匹配要求。随着M形口面唇口占比的增加,进气道出口截面低总压区沿着侧壁逆时针偏转,并且涡旋方向发生改变,总压恢复系数逐渐增大,畸变指数先减小后增加。内通道偏距的增大会进一步加剧地面状态下流场的恶化。In order to find out the cause of bad flow field of the stealthy inlet under the ground state,the flow field structure of the triangular and M-shaped inlets with equal inclined cut surface under the ground state was numerically simulated and analyzed,and the influences of the lip ratio and internal channel offset on the ground working characteristics of the M-shaped inlet were studied.The results showed that a large three-dimensional separated vortex(half flow field)was formed near the inlet symmetry plane in the triangular inlet,while a pair of relatively small vortices were formed at the intersection of the side lip and the upper lip in the M-shaped inlet.Moreover,the distortion index at the outlet of the triangular inlet was too large to meet the inlet/engine matching requirements.With the increase of the proportion of the M-shaped lip,the low total pressure area of the inlet exit section deflected counterclockwise along the sidewall,and the direction of the vortex changed.The total pressure recovery coefficient gradually increased,and the distortion index decreased first and then increased.The increase of internal channel offset could further aggravate the deterioration of flow field under ground conditions.

关 键 词：斜切口面进气道 地面工作状态 三维分离涡 流场结构 畸变指数 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]