范孝华, 杨波, 朱涛, 钟俊. Φ240mm高超声速风洞扩压器设计研究[J]. 空气动力学学报, 2017, 35(5): 633-639. DOI: 10.7638/kqdlxxb-2015.0077
引用本文: 范孝华, 杨波, 朱涛, 钟俊. Φ240mm高超声速风洞扩压器设计研究[J]. 空气动力学学报, 2017, 35(5): 633-639. DOI: 10.7638/kqdlxxb-2015.0077
FAN Xiaohua, YANG Bo, ZHU Tao, ZHONG Jun. Investigation on design of Φ240mm hypersonic wind tunnel diffuser[J]. ACTA AERODYNAMICA SINICA, 2017, 35(5): 633-639. DOI: 10.7638/kqdlxxb-2015.0077
Citation: FAN Xiaohua, YANG Bo, ZHU Tao, ZHONG Jun. Investigation on design of Φ240mm hypersonic wind tunnel diffuser[J]. ACTA AERODYNAMICA SINICA, 2017, 35(5): 633-639. DOI: 10.7638/kqdlxxb-2015.0077

Φ240mm高超声速风洞扩压器设计研究

Investigation on design of Φ240mm hypersonic wind tunnel diffuser

  • 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°-0.8De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。

     

    Abstract: 1-D tube flow method was adopted for the design of Φ240mm hypersonic wind tunnel diffuser at Mach Number 6.0, and numerical simulation was carried out in order to select the configuration of the diffuser. Then, experimental test was used to verify the design method of the diffuser. The results show that, in comprehensive consideration of the flow-field performance of the wind tunnel, the resistance pressure ability, and total pressure recover, the diffuser has single stage compression half-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 diffuser. 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.

     

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