Fig.1

Geometric model of wing-mounted ducted fan configuration

Fig.2

Geometric dimensions of symmetric cross-section for wing-mounted ducted fan configuration

Fig.3

Schematic diagram of wind tunnel test principle

Fig.4

Wind tunnel test setup

Fig.5

Test equipment

Table 1

Specifications of ATI-Delta® six-component balance

Fig.6

Comparison of force signals before and after filtering

Fig.7

Force situation of isolated wing surface test model

Fig.8

Lift and drag characteristic curves of an isolated wing section

Fig.9

Force situation of stand-alone ducted fan test model

Fig.10

Propulsion performance curves of a stand-alone ducted fan

Fig.11

Force situation of wing-mounted ducted fan test model

Fig.12

Propulsion performance curves of an wing-mounted ducted fan

Fig.13

Wind tunnel test section computational domain

Fig.14

Schematic diagram of computational mesh

Fig.15

Comparison of simulated and test values of lift for an wing-mounted ducted fan

Fig.16

Comparison of simulated and test values of thrust for an wing-mounted ducted fan

Fig.17

Comparison between numerical results from different computational domains and tast values

Fig.18

Comparison of pressure contours for two domains at freestream velocity V∞ = 15 m·s-1 and throttle setting 0.8

Table 2

Increments and relative increments of lift and thrust per unit power across throttle setting variations at different freestream velocities

Fig.19

Lift increment per unit power of wing-mounsted ducted fan compared to wing and ducted fan assembly

Fig.20

Thrust increment per unit power of wing-mounsted ducted fan compared to wing and ducted fan assembly

Fig.21

Comparison of pressure contours and stagnation point locations on main wing segment at different freestream velocities under low throttle setting condition （ηi=0.5）

Fig.22

Comparison of pressure contours and stagnation point locations on main wing segment at different throttle settings under a fixed freestream velocity （V∞=6.6 m·s-1）

Fig.23

Comparison of velocity contours within duct internal region at freestream velocities of 19.8 m·s-1 and 25.1 m·s-1

Table 3

Relative increment of combined lift and thrust per unit power across throttle setting variations at different freestream velocities

Fig.24

Relative increment in combined lift and thrust per unit power of wing-mounted ducted fan compared to wing and ducted fan assembly

Fig.25

Influence of throttle setting on coupling effect at a high freestream velocity （25.1 m·s-1）： A comparison of pressure contours and stagnation point locations on main wing

Fig.26

Coupling factors in lift and thrust dimensions of wing-mounted ducted fan compared to wing and ducted fan assembly

Fig.27

Research methodology and framework flowchart