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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,(7):1376~1382
零附加阻力超声速变几何轴对称进气道设计
Design of supersonic axisymmetric variable geometric inlet with zero additional drag
投稿时间:2019-11-20  
DOI:10.13224/j.cnki.jasp.2020.07.005
中文关键词:  轴对称进气道  变几何  零附加阻力  气动设计  流量全捕获
英文关键词:axisymmetric inlet  variable geometry  zero additional drag  ,aerodynamics design  total mass flow capture
基金项目:
作者单位
南向军 Xi'an Aerospace Propulsion Institute,,China Aerospace Science and Technology Corporation,Xi‘an 710100,China 
张浩 Xi'an Aerospace Propulsion Institute,,China Aerospace Science and Technology Corporation,Xi‘an 710100,China 
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中文摘要:
      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。
英文摘要:
      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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