Abstract: An shear stress transport(SST) turbulence model is selected for a variable forward swept wing (VFSW) configuration, and the disperse format of the Navier-Stokes control equations with the finite volume method is employed to analyze numerically the flow fields of all moving wing tips (AMT) for a delta wing aircraft in VFSW configuration. First, the precision of the numerical simulative algorithm is validated by a comparison with the data of a delta wing experimental model without wing leading-edge extension. Second, the characteristics of the AMT for delta wing tailless configuration in a supersonic area are investigated. Finally, the flow fields and operative mechanism of the AMT are analyzed by streamline display. The computational results of the AMT show that the angle of attack has little effect on the characteristics of the AMT, and the yawing moment coefficient of the AMT with the designed maximum deflection angle in the supersonic area is about 0.02, but the yawing moment may be coupled with the rolling moment, and the coupled rolling moment will turn to the opposite direction at a large local angle, while the ultimate cause of the coupled opposite rolling moment is that the rudder loses lift. To sum up, for better linearity of yawing effect and greater yawing efficiency, the AMT is a potential yawing control surface for VFSW configuration provided its negative rolling moment is removed.

Key words: variable forward swept wing, delta wing aircraft, all moving wing tips, flow field, numerical analysis, control characteristics, control surfaces