摘要
垂尾紧靠涡轮喷气发动机尾喷口,随着飞机发动机功率的迅速提高,垂尾声载荷问题的研究愈来愈急需。因空测飞机垂尾声载荷难度较大,费用较贵,本文介绍关于地测声载荷的研究。
The sonic load test data of the vertical tail of F-7 aircraft are analysed and the acoustic pressure distribution law is found from test data.When the sound sensors were installed in a distance less than 5cm from the surface of the tail, the measured data in ground test can substitute those from flight test.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第11期A637-A640,共4页
Acta Aeronautica et Astronautica Sinica
关键词
歼击机
垂尾
声载荷
附面层
jet noise, boundary layer, pressure pulse.
