摘要
利用最新发展的直升机旋翼气动声学程序计算了某模型旋翼桨涡干扰（ＢＶＩ）噪声，叶片表面非定常压力脉动数据由最新实验获得。
A newly developed helicopter rotor aeroacoustics code and newly obtained unsteady surface pressure data on the blade of a model helicopter rotor are used to predict rotor blade vortex interaction noise. Good to fair agreement of the predictions with wind tunnel results both in time history and in directivity of BVI noise has been obtained.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第5期598-600,共3页
Acta Aeronautica et Astronautica Sinica
关键词
噪声预测
声学测量
气动噪声
直升机
noise prediction acoustic measurement aerodynamic noise
