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。
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 above0.97. 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.
作者
安佳宁
AN Jia-ning(Unit 92419 of PLA,Xingcheng Liaoning 125106,China)
出处
《航空发动机》
北大核心
2020年第2期51-55,共5页
Aeroengine
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
S-shaped inlet
total pressure recovery coefficient
distortion index
numerical simulation
matching test
aeroengine
