三维内转式进气道双激波基准流场的设计方法

推进技术 ›› 2015, Vol. 36 ›› Issue (3): 358-364.

三维内转式进气道双激波基准流场的设计方法

卫锋¹,贺旭照^1,2,贺元元¹,吴颖川^1,2

中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000; 中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000,中国空气动力研究与发展中心吸气式高超声速技术研究中心，四川绵阳 621000; 中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000

发布日期:2021-08-15
作者简介:卫锋(1987—)，男，硕士，研究领域为飞行器设计。
基金资助:
国家自然科学基金(91216303；51376192)。

Design Method of Dual-Shock Wave Basic Flow-Field for Inward Turning Inlet

Air-Breathing Hypersonic Technology Research Centre CARDC，Mianyang 621000，China,Air-Breathing Hypersonic Technology Research Centre CARDC，Mianyang 621000，China; Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China,Air-Breathing Hypersonic Technology Research Centre CARDC，Mianyang 621000，China and Air-Breathing Hypersonic Technology Research Centre CARDC，Mianyang 621000，China; Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 探索了一种三维内转式进气道基准流场的设计新思路，基准流场由特征线方法设计的曲面压缩系统组成，包含一道入射激波和一道末端激波，消除了激波在内通道的连续反射。通过数值模拟对该设计思路进行了验证，结果表明:该双激波轴对称基准流场，前缘激波和末端激波入射位置与设计吻合，末端激波入射在肩点且完全实现消波；特征线计算获取的外壁面马赫数分布和CFD结果吻合较好；经过设计，在喉部截面上流动参数比较均匀，总压恢复系数达到0.91；无粘条件下流线追踪进气道完全继承了基准流场的流动特征，流量捕获系数0.999，喉道总压恢复0.88，与同设计条件流线追踪Busemann进气道相当。

关键词: 内转式进气道；双激波；基准流场；特征线方法

Abstract: A new design thought of inner cone flow-field for inward turning inlet is presented. The basic flow-field is designed by rotational method of characteristics，including two shock waves，the leading edge shock wave and the ending shock wave. There is no continuous shock reflection along the internal flow-path. The numerical simulation results show that，the incident locations of the two shock waves are in full compliance with the design and there is no shock reflection at inlet shoulder. And that the distribution of Mach Number along the ramp obtained by the rotational method of characteristics agrees well with the CFD results. The flow parameter at throat is almost uniform and the total pressure recovery coefficient is 0.91. The stream-traced inlet totally inherits the basic flow-field characteristics at inviscid condition. Flow capture coefficient is 0.999. Total pressure recovery coefficient is 0.88，which is almost equal to the value of stream-traced Busemann inlet at the same design condition.

Key words: Inward turning inlet；Dual-shock wave；Basic flow-field；Rotational method of characteristics

卫锋,贺旭照,贺元元,吴颖川. 三维内转式进气道双激波基准流场的设计方法[J]. 推进技术, 2015, 36(3): 358-364.

WEI Feng¹,HE Xu-zhao^1,2,HE Yuan-yuan¹,WU Ying-chuan^1,2. Design Method of Dual-Shock Wave Basic Flow-Field for Inward Turning Inlet[J]. Journal of Propulsion Technology, 2015, 36(3): 358-364.

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