Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers
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摘要: 在Φ3.2m风洞研制了基于双力矩电机同步驱动的机动进气道试验装置，模拟战斗机快速俯仰等机动过程和进气道不同工作条件，建立了战斗机进气道非定常性能试验方法。通过验证试验研究了战斗机模型快速俯仰机动过程中进气道性能变化的基本规律，获得了进气道动态周向畸变、紊流度等部分流场畸变参数的变化特性，验证了战斗机进气道低速风洞非定常性能试验技术的可行性。Abstract: A test facility was developed in the Φ3.2m wind tunnel, which is driven by two moment electromotors and used to simulate inlet working conditions of the fighter during high maneuvers. The unsteady test method for research on the inlet flow characteristics was established. Based on results of the validating test, the inlet flow characteristics during maneuvers with rapidly changing angle of attack were studied. Some unsteady features, such as the circumferential distortion and turbulence, were obtained from the tests. All these results prove the feasibility of the test technology on studying the unsteady characteristics of the fighter plane inlet flow during maneuvers in the low speed wind tunnel.
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Key words:
- fighter plane /
- inlet /
- unsteady /
- test technology /
- distortion
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图 4 进气道出口截面测点分布
Figure 4. Pressure point distribution on interface of inlet and engine
图 10 总压恢复随迎角变化的关系
Figure 10. Total pressure recovery ratio changing with angle of attack
表 1 迎角精度
Table 1. Measurement precision of AOA
起始
角度/(°)平均运动
速率/(°/s)运动
时间/s编码器
测量值/(°)电位计
测量值/(°)Optotrak
测量值/(°)0 40 0.75 30.01 30.03 30.05 0 20 1.5 30.01 30.03 30.03 0 60 0.75 45.01 45.04 60.30 0 40 1.5 60.01 60.03 60.20 
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