Numerical Analisys of Delta Wing 65 and 75 Backward Angle Degrees in Different Angles of Attack and Mach numbers

Steady flow over a delta-wing at 65 and 75 sweep angles with a flat cross-section and a leading-edge that is not quite sharp is analysed in different AOAs and flow regimes. Flow pattern on the upper-surface of the wing, is divided to 6 categories, based on the vertical components of the AOA and Mach number on the leading-edge. The aerodynamic coefficients of the wing are calculated for all cases and the related graphs and flow patterns are investigated. The calculated coefficients are compared with the published cases from previous studies and the observed differences based on various Mach numbers and AOAs are discussed. The results indicates that by increasing the Mach number, the lift and drag coefficients are increased. Pressure contours shows that by increasing the AOA, the pressure on the upper-surface and lower-surface is decreased and increased respectively. A large part of the pressure drop is due to the leading edge vortices on the wing-surface. In flow speeds over Mach=2 the leading edge speed become supersonic and expansion waves propagated from the leading edge accelerate the flow, and as the AOA increase, the shock-wave power is increase and cause a growth to the lift and drag coefficients.