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针对一种双下侧布局带泄流腔的二元进气道进行了试验研究.试验时,来流速度范围Ma=2.0~3.5,姿态角范围为α=-4°~10°,β=0°~4°.试验获得了进气道的反压特性曲线、速度特性曲线、迎角特性曲线和侧滑角特性曲线.分析表明,随着来流速度和迎角的增加,进气道的流量系数先增加,在设计点达到最大,之后由于弹身头部激波的影响略有减小.侧滑时两侧进气道气流状态不同,工作范围由性能较低的迎风侧进气道来决定.另外,通过分析进气道的沿程静压分布曲线,说明泄流腔结构能使结尾激波停留在泄流腔边缘,扩大了进气道的工作范围.
Experimental results show that the flow velocity range Ma = 2.0 ~ 3.5, the attitude angle range is α = -4 ° ~ 10 °, β = 0 ° ~ 4 °.The back pressure, speed characteristic, angle of attack curve and side slip angle characteristic curve of the inlet were obtained by experiments.The analysis shows that with the increase of incoming velocity and angle of attack, Of the flow coefficient first increased, reaching the maximum at the design point, then slightly reduced due to the impact of the shock head shock.Slippage on both sides of the inlet airflow state is different, the working range from the lower windward side of the intake In addition, by analyzing the static pressure distribution curve along the inlet, it shows that the structure of the discharge chamber can make the ending shock wave stay at the edge of the discharge chamber and enlarge the working range of the inlet.