Design of supersonic axisymmetric variable geometric inlet with zero additional drag

NAN Xiangjun; ZHANG Hao

doi:10.13224/j.cnki.jasp.2020.07.005

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Design of supersonic axisymmetric variable geometric inlet with zero additional drag

更新时间：2026-07-07

- Design of supersonic axisymmetric variable geometric inlet with zero additional drag
- Vol. 35, Issue 7, Pages: 1376-1382(2020)
- 作者机构：
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- DOI：10.13224/j.cnki.jasp.2020.07.005
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- Published：2020
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南向军, 张浩. 零附加阻力超声速变几何轴对称进气道设计[J]. 航空动力学报, 2020, 35(7): 1376-1382.

doi: 10.13224/j.cnki.jasp.2020.07.005
南向军, 张浩. 零附加阻力超声速变几何轴对称进气道设计[J]. 航空动力学报, 2020, 35(7): 1376-1382. DOI： 10.13224/j.cnki.jasp.2020.07.005.

doi: 10.13224/j.cnki.jasp.2020.07.005 DOI：

摘要

为了解决进气道压缩量与来流马赫数在宽马赫数工作范围匹配难的问题，开展了流量几乎可以全捕获的变几何进气道设计探索研究，从气动理论分析得到进气道设计需满足的理论关系式，据此开展了进气道气动型面设计，并研究了相应的变几何调节规律，利用数值模拟研究了进气道的气动性能，来流马赫数在12～40范围内流量系数可以达到099以上。初步研究表明通过精确匹配来流马赫数、收缩比和变几何调节规律，可以获得宽范围内流量全捕获的进气道气动型面，设计的唇口压缩面具有“S”形特征。

Abstract

In order to solve a difficult problem of inlet that its compression doesnt well match with free Mach number within large Mach number range

an inlet with total mass capture was explored. Theory relations that should be met in inlet design process were obtained according to aerodynamics analysis. Based on these relations

an inlet example was designed and its variable geometry law was gotten. Numerical simulation was used to research the flowfiled and performance of the inlet

whose mass flow rate could be over 099 from Mach number 12 to 40. Preliminary results show that an inlet with total mass flow capture within wide Mach number can be designed by matching the free Mach number

contraction ratio and variable geometry law exactly

and cowl wall shape has characteristic of “S”.

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Related Institution

中国航天科技集团有限公司西安航天动力研究所

南京航空航天大学能源与动力学院

Aeronautics and Astronautics Engineering College, Airforce Force Engineering University

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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