增升装置连式襟翼噪声抑制技术试验研究

针对L1T2翼型增升装置襟翼边缘噪声的特征，设计了两种不同偏角下的连式襟翼模型，通过声学风洞试验，开展了连式襟翼的襟翼边缘噪声的抑制技术研究。试验采用传声器相位阵列以及远场线阵，结合波束形成、声压级积分、频谱分析等方法，测量了不同襟翼偏角和迎角下连式襟翼的降噪效果。研究表明：襟翼偏度30°时，襟翼边缘噪声是L1T2翼型増升装置襟翼噪声的主要噪声源，集中在5kHz-16kHz频率范围内；襟翼偏度30°时，连式襟翼的噪声效果明显，部分频率下的最大降噪量可达9dB；此外，连式襟翼的降噪效果随着迎角的增大略有减小。

Experiment research of the high lift device noise reduction technology based on Continuous mold-line links

Based on the noise mechanism and character of the L1T2 high lift device, two types of continuous mold-line links(CML) was designed to reduction the flap side edge noise. The noise reduction technology based on continuous mold-line links was verified in the aeroacoustic wind tunnel. The noise data of the continuous mold-line links model under different flap angle and attack angle was tested by microphone phased array and far-field microphones, and analyzed by means of beamforming, sound pressure level integration and spectrum analysis. The test results showed that the noise generated by the flap side edge dominated in the frequency range of 5kHz to 16kHz, was the major sour of flap noise under the 30° flap angle. The continuous mold-line links could reduce the flap side edge noise obviously in this frequency range under the 30° flap angle, the most noise reduction could reach 9dB. Comparing the performance of noise reduction of continuous mold-line links under different flap angle and attack angle, the noise reduction level of continuous mold-line links was found to be related to the flap angle and attack angle. For the current research, the noise reduction level increase with the flap angle, and decrease with the attack angle.