Fig.1

Schematic diagram of reconstruction value calculation on the left side of grid cell interface

Fig.2

Grids used in simulation calculation

Table 1

Trimmed collective pitches of Harrington-2 rotor case［8］

Fig.3

Comparison of hover performance of Harrington-2 rotor

Fig.4

Comparison of normal force coefficients of some blade sections of 7A rotor

Fig.5

Microphone locations for OLS rotor experiment

Fig.6

Comparison of sound pressure time history at some observation points of OLS rotor case

Table 2

Trim solutions of XH-59A helicopter forward flight case［2］

Fig.7

Schematic diagram of observation points for XH-59A helicopter aeroacoustics calculation

Fig.8

Wake of XH-59A helicopter flow field （isosurface of Q=0.002）

Fig.9

Curve of rotor thrust coefficient changing with azimuth under different calculation conditions

Fig.10

Curve of lift coefficients changing with azimuth on blade characteristic section

Fig.11

Distribution of SPL on hemispherical 5R from rotor center

Fig.12

Sound pressure time history of rotor noise at characteristic observation points

Fig.13

Noise spectrum at characteristic observation points

Fig.14

Comparison of SPLs at observation points under different calculation conditions

Fig.15

Geometry of blade with different types of tip shapes

Fig.16

Diagram of wake flow field （isosurface of Q=0.002）

Fig.17

Curve of rotor aerodynamic characteristics changing with azimuth at different anhedral angles

Fig.18

Comparison of acoustic characteristics at different anhedral angles

Fig.19

Comparison of SPLs at observation points at different anhedral angles

Fig.20

Top view of wake flow field （isosurface of Q=0.002）

Fig.21

Curve of rotor aerodynamic characteristics changing with azimuth at different dualswept angles

Fig.22

Comparison of acoustic characteristics at different dualswept angles

Fig.23

Comparison of SPLs at observation points at different dualswept angles