Figures of the Article

• Computational grid of the airfoil
• Baseline airfoil
• Comparison of the trailing-edge shapes for different N
• Comparison of pressure distributions on the airfoils for different N (α = 1.5°)
• Comparison of the trailing edges for different thickness
• Comparison of pressure distributionsfor different trailing-edge thickness Δy₁ (C_L = 0.97)
• Lift force comparison for different trailing-edge thickness
• Drag divergence comparison for different trailing-edge thickness (Re=4×10⁶)
• Drag divergence curve comparison for different trailing-edge thickness (Re=2×10⁷)
• Reynolds number effect for the drag reduction of airfoils with different trailing-edge thickness (Ma = 0.72)
• Reynolds number effect for the drag reduction of airfoils with different trailing-edge thickness (Ma = 0.5)
• Reynolds number effect for the pitching moment incre-ment of airfoils with different trailing-edge thickness (Ma = 0.72)
• Comparison of airfoil shapes with different thickness
• Comparison of pressure distributions for airfoils with different thickness (C_L = 0.97)
• Lift-drag polar curve comparison for airfoils with different thickness (Ma = 0.72)
• Drag divergence curve comparison for airfoils with different thickness (C_L = 0.97)
• C_p contour of baseline wing-fuselage-nacelle-pylon shape
• Variation of the trailing-edge thickness increment along the spanwise direction
• Comparison of spanwise lift coefficient distributions before and after the DTE modification
• Comparison of pressure distributions before and after the DTE modification