Abstract: Support interferences of low-aspect-ratio flying-wing at M=0.6, 0.9 1.5 are calculated by means of numerical simulation methods, both near-field interference and far-field interference are concerned, and attempt is made to analyse mean flow distortion distribution for the model. Results show that, drag coefficient and pitching moment coefficient of far-field interference account about 30% of the total support interference while lift coefficient account about 20% at M=0.6. For Mach number 0.9, angle of attack 2°, drag coefficient of far-field interference account 40%, and far-field interference make the vortex breakdown location move ahead at the angle of attack 18°. Far-field interference can be ignored at M=1.5. It's hard to get the distortion of Mach number and angle of attack (Δ M and Δ α) at subsonic speed (M=0.6); when upstream become M=0.9, support interference affects the shock position, and the surface pressure coefficient differences are sensitive with Mach number, support interference decrease the Mach number for about 0.02 and decrease the angle of attack for 0.1° on the model surface.