一种轴对称变几何进气道气动设计及性能分析  

Aerodynamic design and performance analysis of an axisymmetric variable geometry inlet

作　　者：宁啸天 辜天来 田亚洲 刘甫州 袁化成[1] NING Xiaotian;GU Tianlai;TIAN Yazhou;LIU Fuzhou;YUAN Huacheng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing210016,China;Department of Research and Development,China Academy of Launch Vehicle Technology,Beijing100076,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]中国运载火箭技术研究院研究发展部,北京100076

出　　处：《固体火箭技术》2021年第6期783-792,共10页Journal of Solid Rocket Technology

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

摘　　要：采用基于雷诺时均方程的数值模拟方法,对一种Ma=4级的轴对称超声速变几何进气道气动方案设计及其性能分析开展了研究。首先,基于总体设计约束,构建了进气道3种外压缩气动方案、5种内压缩设计方案、多种不同的扩压器设计方案,对其不同来流马赫数下的气动性能进行了数值模拟对比分析,给出了典型几何设计参数对该类超声速轴对称进气道气动性能的影响规律;据此,获得了一种三级锥外压缩、扩压段面积与中心线变化规律前后缓急相当的唇罩可动式轴对称超声速可调进气道气动设计方案及其几何调节规律。其次,对所设计的可调进气道开展了气动性能分析研究,数值模拟的结果显示:在不同的马赫数状态下,该可调进气道的捕获流量满足预期设计需求,Ma=2和Ma=4时,进气道出口的总压恢复系数分别为0.82和0.45。An axisymmetric supersonic inlet with a design Ma=4 was numerically investigated by RANS,focusing on the de⁃sign of aerodynamic profile,the case of variable geometry,and the aerodynamic performance of the inlet.Based on the overall de⁃sign constraints,three external compression aerodynamic schemes,five internal compression designs and different diffuser designs were constructed.Aerodynamic performance of supersonic axisymmetric inlet under different Mach numbers was numerically simula⁃ted and analyzed comparatively.The effects of typical geometric design parameters on the aerodynamic performance were investiga⁃ted.The aerodynamic design programs and the geometry regulating laws were obtained for the axisymmetric variable geometry inlet with a movable lip,which was also featured by a tertiary structure of extrapyramidal compression and similar variation laws between the centerline and the expansion section area.Furthermore,the aerodynamic characteristics of the proposed inlet being capable in mass capture rate adjustment were analyzed.The results show that the axisymmetric variable geometry inlet with a movable lip can meet the requirements of flow coefficient at different Mach numbers.The total pressure recovery coefficient at the exit is 0.82 when the inlet works at freestream Mach 2,and it decreases to 0.45 at Mach 4.

关 键 词：超声速进气道 轴对称进气道 变几何 数值模拟 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]