Numerical analysis of the effects of sweep angle and sharpness of leading edge on Aerodynamic behavior of delta wing

Delta wing is studied in several Mach numbers, sweep angles, sharp and curved edges of attack. Algorithm of flow on upper side of the wing is studied and illustrated. Algorithm of flow is compared with the elder studies and changes of these options by Mach number and angle of attack and sweep angle is determined. Illustrations show that on the upper side of the delta wing, a vortex arises that by increasing Mach number, stretches and comes near the wing. Also addition to the primary vortex, secondary vortex arises. In Mach numbers up to 1.2 edge of attack becomes supersonic and expansion waves, accelerate the flow. In higher angles of attack, vortex breakdown occurred that in different Mach numbers and different angles of attack is studied.