AERODYNAMIC PERFORMANCE OF SAAB JAS GRIPEN C-LIKE FIGHTER AIRCRAFT WITH CANARD-WING DELTA

The aerodynamic performance of an aircraft, especially fighter aircrafts configured with wing canard-deltas, produced a phenomenon of airflow that could form a vortex core which could produce suction giving additional lifts. Wing-canard delta configuration was able to create different lift distribution to the angle of attack where the stall occurred at a higher angle of attack than the conventional wing aircraft configuration. This study investigated the aerodynamic performance of wing canard delta configurations in the Saab JAS Gripen C-like model which had a different wing shape on its wing planform than other fighter aircraft. To obtain values in the form of axial velocity plots along the vortex core, trajectory vortex core, the pressure coefficient distribution CFD analysis utilized ANSYS FLUENT software, where these results were challenging to obtain with water tunnels or wind tunnels. The results showed that the Saab JAS Gripen C-like model stalled at a 40° angle of attack (AoA) with a maximum CL value of 1.431 with a slope of the CL curve of 2.995 / rad. The value of the lift to drag ratio was highest at an angle of 5° with a lift of 11.58 times the drag value. The location of the vortex core height was higher, and the width of the vortex core tended to move away from the fuselage every time the angle of attack increased. In canard vortex core, maximum axial speed increase occurred at an angle of 30° with a value of 1.027 times the speed of the free stream while on the wing vortex core occurred at an angle of 40° for 1.835 times the speed of the free stream.