Fig.1

Scheme of 5.5 m×4 m aeroacoustic wind tunnel

Fig.2

Structure of test model （Full model）

Fig.3

Installation and relative locations of test model and microphone arrays

Fig.4

Farfield noise for various high-lift device/wing configurations （0° angle of attack， No.20 microphone）

Fig.5

Effects of angles of attack on farfield noise of high-lift device （landing configuration， No.20 microphone）

Fig.6

Noise source localization for landing configuration at various angles of attack （80 m/s wind speed， 2 175 Hz）

Fig.7

Effects of wind speeds on farfield noise of high-lift device （0°/9° angles of attack， No.20 microphone）

Fig.8

Noise source localization for landing configuration atvarious wind speeds （0° angle of attack， 3 150 Hz）

Fig.9

Effects of wind speed on farfield noise of high-lift device （6° angle of attack， landing configuration）

Fig.10

Noise source localization for landing configuration at various frequencies and wind speeds （6° angle of attack，40 m/s and 80 m/s‍）

Fig.11

Noise source localization for landing configuration at various frequencies and wind speeds （6° angle of attack，40 m/s and 60 m/s）

Fig.12

Comparison of farfield noises for high-lift device in different directions （landing configuration，80 m/s wind speed， transverse profile）

Fig.13

Comparison of farfield noises for high-lift device in different directions （landing configuration， 80 m/s wind speed， flyover profile）

Fig.14

Mach number similarity for full model with landing configuration （0° angle of attack）

Fig.15

Mach number similarity for full model with landing configuration （6° angle of attack）

Fig.16

Noise source localization for landing configuration at various frequencies （6° angle of attack， 80 m/s wind speed）

Fig.17

Mach number similarity for full model with landing configuration （9° angle of attack）

Fig.18

Mach number similarity for full model with landing configuration based on band division correction （9° angle of attack）

Fig.19

Noise source localization for landing configuration at various frequencies （0° angle of attack， 40 m/s wind speed）

Fig.20

Mach number similarity for full model with taking off configuration （0° angle of attack）

Fig.21

Mach number similarity for half model with landing configuration （0° angle of attack）

Fig.22

Mach number similarity for half model with landing configuration （9°angle of attack）

Fig.23

Mach number similarity for half model with landing configuration based on band division correction （9° angle of attack）

Fig.24

Noise source localization for landing configuration at various frequencies （half model， 0° angle of attack， 80 m/s wind speed）

Fig.25

Comparison of similarity transformation and frequency correction according to St and He