Analysis of subsonic flow over delta winged aircraft

Abstract

Aerodynamic analysis on a delta wing is carried out in the present work. Many aircrafts, bombers and fighter jets use delta winged aircrafts. Delta wing aircrafts have the characteristics of producing a greater lift at very small angles of attack (AoA) even at lower velocities. Highly swept delta wings experience greater lift due to the vortex lift at high angle of attack. The phenomenon of vortex breakdown is noticed in delta wings which leads to a reduction of the vortex lift and leads to the instability of the aircraft which is dangerous. The present study deals with the analysis of the pressure contours and the velocity contours during a subsonic flow over a delta wing. The computational analysis is carried out in ANSYS FLUENT. The effect of the lift coefficient with angle of attack is also studied. The critical angle of attack which gives a maximum lift is observed for the model chosen. The pressure coefficient variation across the span at different chord locations are also computed. The results of the analysis has proved the presence of vortex lift which increases the lift values at higher angle of attack. The wing is experiencing an increased pressure below, when compared to the pressure above the wing. The nature of the pressure coefficient drop across the span along the chord length is presented.