Fig.1

Sketch of distributed propulsion wing and its rectangle ducted fan unit

Fig.2

Sectional airfoil of outer wall surface of rectangle ducted fan unit

Fig.3

Decomposition of inner wall surface of rectangle ducted fan unit

Fig.4

Parametric model of rectangle-to-circle inlet and circle-to-rectangle outlet

Fig.5

NASA ducted propeller geometry

Fig.6

Sketch of computational mesh model for MRF method

Fig.7

Sketch of computational mesh model for MSM

Table 1

Comparison of NASA ducted propeller propulsive performance between numerical results and experimental data

Fig.8

Sketch of varied-camber rectangle ducted fan models

Fig.9

Comparison of pressure distribution at center-cross section of varied-camber rectangle ducted fan models

Fig.10

Comparison of pressure distribution at center-cross section between varied-camber rectangle ducted fan models and their related conventional wings

Fig.11

Loose coupling design flowchart of propulsion wing unit

Fig.12

Design optimization process of rotor blade of ducted fan

Fig.13

Sketch of equivalent airfoils of rectangle duct wall

Fig.14

Multi-level collaborative optimization design framework of rectangle duct wall

Fig.15

Sketch of designed rectangle ducted fan model and distributions of chord length and twist angle along rotor blade

Fig.16

Computational mesh of quasi-two-dimensional model for rectangle ducted fan

Table 2

Verification of propulsive/aerodynamic coupling performance of quasi-two-dimensional model for propulsion wing unit

Fig.17

Geometry of test model of rectangle ducted fan and comparison with quasi-two-dimensional model

Fig.18

Photos of wind tunnel test of rectangle ducted fan

Fig.19

Computational mesh of test model of rectangle ducted fan

Fig.20

Propulsive/aerodynamic coupling performance at hovering state

Fig.21

Sketch of pressure tap arrangement on symmetrical duct profile

Fig.22

Comparison of pressure distribution coefficient on duct wall （V=10 m/s， n=10 000 r/min， α=4°）

Fig.23

Comparison of pressure distribution coefficient on duct wall （V=20 m/s， n=10 000 r/min， α=4°）

Fig.24

Comparison of pressure distribution coefficient on duct wall （V=30 m/s， n=10 000 r/min， α=4°）

Table 3

Propulsive/aerodynamic characteristic coefficients of propulsion wing unit under different inflow velocities （n=10 000 r/min， α=4°）

Fig.25

Variation trend of static pressure on test duct wall with variation of inflow velocities （n=10 000 r/min， α=4°）

Fig.26

Sketch of flow field characteristics

Fig.27

Comparison of pressure on duct wall under different angles of attack （n=10 000 r/min， V=30 m/s）