[commander-plane]

Hi, I'm working on the graduation project to get the bachelor's degree in aeronautical engineering. The project is an aerodynamic analysis of the F-15 wing by using Ansys fluent 18.2.
But at maximum AOA I got CL of 0.45 only and it is known that the CL of Fighter aircrafts are between 1.8 and 3.
I tried videos on Youtube but nothing new.
Please help !

Boundry condition type: Rectangular include: inlet, outlet, symmetry (root face) and wing surface (upper and lower)

viscous model: k-e relizable
air characteristics: by default
inlet type: velocity inlet with velocity say 100 m/s or any velocity .. and supersonic/initial gauge pressure=0
outlet type: pressure outlet with value=101325 Pa (sea level condition)
reference value is ok i choose inlet and insert aera=29.7 m^2 and length=3.84 m
methods type SIMPLE and all under second order for high accuracy
iteration is 1200 until values converted

note: i use design moduler for changing the angle of attack, also the maximum angle of attack is 22 degree with lift coefficient = 0.45 only