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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。
Based on the comprehensive wind tunnel measurement, manometry and pulsating pressure measurement and analysis techniques, a wind tunnel verification test method for the hypersonic vehicle through-flow ratio model is given. Axisymmetric layout and lift body shape model are selected. Through the wind tunnel verification test, the flow and aerodynamic characteristics of the model under different height conditions of the throat of intake air are studied, and the Reynolds number is changed under given inlet throat height Effect on the aerodynamic characteristics of the model. The results show that this verification test can effectively simulate the conditions of flow passage under different conditions in the wind tunnel and achieve the purpose of studying the aerodynamic characteristics of the model and optimizing the design of the air intake. For the lift body configuration, The flow characteristics have little effect and can provide some basis for simulating actual flight conditions. Related data processing and analysis methods can be used as a reference for the wind tunnel test of such models.