Development of Counter Rotating Axial Fan Turbojet Engine for Supersonic Unmanned Plane

机译：超音速无人机逆旋转轴向粉机涡轮喷钟发动机的开发

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performance at on- and off-design conditions, On-design analysis shows that the airflow rate and pressure ratio had amounts to about 3.45 kg/sec and 2,8, respectively Off design analysis indicates that total performance of counter rotating axial fan is governed by 2nd Fan operation. The performance of 1st Fan obeys to that of 2 nd Fan,

机译：在开启和非设计条件下的性能，设计分析表明，气流率和压力比具有约3.45千克/秒，2,8分别关闭设计分析表明逆旋转轴向风扇的总性能受到治理通过第二风扇操作。第一个风扇obeys到2个粉丝的表现，

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《AIAA/ASME/SAE/ASEE Joint Propulsion Conference》|2007年||共6页
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Ryojiro Minato; Toyohiko Ota; Kiyoshi Fukutom; Nobuhiro Tahatsugu; Kazuhide Mizobata; Takayuki Kojima; Hiioaki Kobayashi;
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中图分类 V43-532;
关键词
Supersonic Unmanned Plane; Counter Rotating Axial Fan; Off-design performance;

机译：超音速无人机;逆旋转轴流风扇;非设计性能;

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4. Development of Counter Rotating Axial Fan Turbojet Engine for Supersonic Unmanned Plane [C] . R. Minato, T. Oota, K. Fukutomi, AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit . 2007

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Development of Counter Rotating Axial Fan Turbojet Engine for Supersonic Unmanned Plane

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