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航空学报  2014 

高超声速飞行器通流模拟方法与风洞验证技术

DOI: 10.7527/S1000-6893.2014.0122, PP. 2932-2938

Keywords: 高超声速飞行器,轴对称进气道,升力体,通流模拟,风洞试验,脉动压力测量,气动特性

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Abstract:

综合运用风洞测力、测压和脉动压力测量与分析技术,给出了一种高超声速飞行器通流缩比模型风洞验证试验方法.选取轴对称布局和升力体外形模型,通过风洞验证试验,研究了不同进气道喉道高度条件下模型通流状况与气动特性,以及在给定进气道喉道高度条件下改变雷诺数对模型气动特性的影响.研究结果表明该验证试验可有效实现风洞模拟进气道不同工况通流条件,达到研究模型气动特性和优化进气道设计的目的;对于升力体布局外形,雷诺数的变化对模型的通流特性影响很小,可为模拟实际飞行条件提供一定依据.相关的数据处理与分析方法,可作为开展此类模型风洞试验的借鉴.

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