Fig.1

Various distributed ducted fan aircraft design［7-12］

Fig.2

Over-the-wing single ducted fan-wing section coupling configuration

Fig.3

Grid of single ducted fan-wing section coupling configuration

Fig.4

Boundary condition setting for ducted fan-wing coupling configuration

Fig.5

Velocity distribution comparison at three locations on upper surface of the mid-section wing of a single ducted fan-wing section coupling configuration at different rotation speeds

Fig.6

Schematic diagram of two boundary condition methods

Fig.7

Velocity distribution of front and rear interfaces obtained by different methods

Fig.8

Comparison of lift coefficients calculated by several methods

Fig.9

Comparison of pressure coefficients of wing calculated by several methods

Fig.10

Comparison of drag coefficients calculated by several methods

Fig.11

Front view of intake surface pressure coefficient calculated by MRF method and the difference between intake surface pressure coefficient calculated by four traditional momentum source methods and MRF method surface pressure coefficient

Fig.12

Schematic diagram of solution process of the novel momentum source method

Fig.13

Schematic diagram of grid of MRF method and novel momentum source method

Fig.14

Schematic diagram of MRF method and novel momentum source method

Fig.15

Axial velocity of front and rear interfaces of α=4° flow field calculated by MRF method

Fig.16

Distribution of turbulent kinetic energy and turbulent eddy dissipation at rear interface of α=4° flow field calculated by MRF method

Fig.17

Comparison between new momentum source method and MRF method in calculating lift and drag coefficient of single ducted fan-wing section coupling configuration

Fig.18

Schematic diagram of FFD control points on upper surface of airfoil

Table 1

Movement range of point 1

Table 2

Movement range of point 2 to point 6

Fig.19

Relative error statistics of aerodynamic coefficients as disturbance amplitude changes

Fig.20

Axial velocity for front interface at α = 4°and 10°

Fig.21

Front interface axial velocity distribution at 9 000 r/min and 15 000 r/min

Fig.22

Back interface axial velocity distribution at 9 000 r/min and 15 000 r/min

Fig.23

Comparison of lift and drag coefficients obtained using MRF method and the novel momentum source method at 9 000 r/min and 15 000 r/min

Fig.24

Grid of the distributed ducted fan-wing coupling configuration

Fig.25

Schematic diagram of principle of single source method and multi-source method

Fig.26

Comparison of lift coefficient calculation using MRF method， single source method and multi-source method

Fig.27

Comparison of drag coefficient calculation using MRF method， single source method and multi-source method

Fig.28

Comparison of pitching moment coefficient calculation using MRF method， single source method and multi-source method

Fig.29

Comparison of front and rear interface velocity distribution between single ducted fan-wing section coupling configuration and distributed ducted fan-wing coupling configuration

Table 3

Thrust performance of single ducted fan-wing section coupling configuration

Table 4

Thrust performance of distributed ducted fan-wing coupling configuration