中文摘要：

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.

英文摘要：

The wind tunnel validation tests for the reduced model of hypersonic vehicle are presented in this paper,by comprehensively utilizing wind tunnel force measurement,pressure measurement and fluctuating pressure measurement and analysis technique.The through-flow status and aerodynamic characteristics of the model at different inlet throat heights,and Reynolds numbers＇ effects on aerodynamic characteristics of the model in the given inlet throat height are studied by wind tunnel validation tests for the axisymmetric configuration model and lifting-body configuration model.The results show that the validation tests can effectively carry out through-flow conditions of inlet in different working statuses by means of wind tunnel simulation,and the purposes of studying aerodynamic characteristics of the model and optimizing the design of inlet are achieved.Furthermore,Reynolds numbers＇ effects on through-flow characteristics of the lifting-body configuration model are very slight,which can provide some foundation for actual flight condition simulation.The interrelated data processing and analysis methods can be used in the similar condition of the model designs of wind tunnel test.