Previous analyses of boundary layer trailing edge noise for large rotors have used zero blade angle of attack as input data. Attention is presently given to the important effects of blade angle of attack changes on rotor trailing edge noise in the case of a UH-1 helicopter. The primary effect is in the low to mid-frequency range, where noise level increases with angle of attack.
Effect of angle of attack on rotor trailing-edge noise
AIAA Journal ; 22
1984-12-01
Miscellaneous
No indication
English
Effect of angle of attack on rotor trailing-edge noise
AIAA | 1984
|Helicopter rotor trailing edge noise
AIAA | 1981
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British Library Conference Proceedings | 2004
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