带多个进气道的导弹通气模型测力试验技术研究

Force measurement test technique research of flowthrough model of the multiinlet missile

高速风洞通气模型试验是研究发动机进气对飞行器气动特性影响的重要手段之一。带多个进气道的大长细比导弹通气模型测力试验结果与国外参考值具有很好的一致性。试验中影响试验数据质量的几个关键技术问题及其解决措施有内流管道设计要求、流量调节位置的选取原则以及通气面积比的确定等。

Force measurement test of flowthrough model in high speed wind tunnel is an important means of researching influence of inlet airflow on aerodynamic characteristics, and has a great perspective of application. This paper presents several key technical problems and solution relevant to data quality of missile flowthrough model with several inlet and great fineness ratio, including requirements of indrafttube's design, principle of opting for flowcontroller's position and determination of flowthrough area ratio. It is shown that the test results are in good agreement with foreign reference results.