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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。
High-speed wind tunnel ventilation model test is one of the important means to study the influence of engine intake on aerodynamic characteristics of aircraft. The results of the force-measuring test of large-aspect-ratio missile ventilation model with multiple inlet ports have good consistency with foreign reference values. Several key technical problems that affect the quality of test data and their solutions are the design requirements of inflow pipe, the selection principle of flow regulation position and the determination of ventilation area ratio.