Φ240mm高超声速风洞扩压器设计研究  

Investigation on design of Φ240mm hypersonic wind tunnel diffuser

作　　者：范孝华[1] 杨波[1] 朱涛[1] 钟俊[1] 

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000

出　　处：《空气动力学学报》2017年第5期633-639,644,共8页Acta Aerodynamica Sinica

摘　　要：采用一维管流方法对口径为Φ240mm、马赫数6.0的自由射流高超声速风洞扩压器进行设计,运用数值模拟方法对扩压器结构形式进行了筛选,并通过试验验证扩压器设计方法的有效性。结果表明:综合考虑风洞流场品质、扩压器抗反压能力以及扩压器总压恢复等指标,确定单级15°-0.8 De扩压器方案为最优设计方案;该方案扩压器的试验与数值模拟结果吻合较好,能够使风洞正常起动,并长时间维持风洞正常运行;筛选得到的扩压器方案可用于风洞建设,其设计方法可为同类高超声速风洞扩压器的研制提供参考。1-D tube f low method was adopted fo r the design of Ф240 mm hypersonic wind tunnel diffuser at Mach Number 6. 0, and numerical simulation was carried out in order to select the configuration of the dif fuser. T h e n,experimental test was used to verify the design method of the dif fuser. The results show th a t, in comprehensive consideration of the flow- f ieldperformance of the wind tu n n e l, the resistance pressure a b i l i ty, and total diffuser has single stage compression hal--cone angle being 15° and second throat diameter being 0.8De（the exit diameter of the nozzle）. The experimental results of the optimal diffuser agree well with corresponding numerical ones. The hypersonic wind tunnel can start smoothly and maintain long-time operation with this dif fuser. The optimal diffuser design can be implemented in the construction of new wind tunnel and the design method of the diffuser provides a reference for the development of similar diffusers in hypersonic wind tunnel.

关 键 词：自由射流 高超声速风洞 扩压器 抗反压能力 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]