| 安佳宁.亚声速无人机背部S 弯进气道设计与试验[J].航空发动机,2020,46(2):51-55 |
| 亚声速无人机背部S 弯进气道设计与试验 |
| Design and Test of S-shaped Inlet at Back of Subsonic Unmanned Aerial Vehicle |
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| DOI： |
| 中文关键词: S 弯进气道 总压恢复系数 畸变指数 数值模拟 匹配试验 航空发动机 |
| 英文关键词:S-shaped inlet total pressure recovery coefficient distortion index：numerical simulation matching test aeroengine |
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| 中文摘要: |
| 为了优化亚声速无人机进气道的性能，完成了1 种背部S 弯进气道设计。通过合理控制中心线形状和截面积变化率完
成了内型面设计，利用内、外流场耦合仿真得到了该进气道的最佳工作点和速度、迎角、侧滑角特性。数值仿真结果表明：总压恢复
系数达到0.97 以上。利用试制的玻璃纤维进气道与发动机进行了地面静止吸气状态下的匹配试验，试验结果表明：在地面静止吸
气状态下发动机稳定工作裕度和熄火特性均满足设计要求，推力损失小于0.032。 |
| 英文摘要: |
| In order to optimize the inlet performance of the subsonic Unmanned Aerial Vehicle （UAV），a kind of S-shaped inlet at
back was designed. The interior surface design was accomplished by reasonably controlling the change rate of centerline shape and crosssectional
area. The optimum working point，velocity，angle of attack and sideslip characteristics of the inlet were obtained by the coupling
simulation of internal and external flow field. The numerical simulation results show that the total pressure recovery coefficient is above
0.97. Using the glass fiber inlet and the engine，the matching test was carried out under the static inspiratory condition of the ground. The
test results show that the stable operating margin and flameout characteristics of the engine meet the design requirements under the static
inspiratory condition of the ground，and the thrust loss is less than 0.032. |
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