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+//consider a NACA-23012(finite wing)
+Re=5*10^6;//reynold's number
+e=0.95;//span efficiency factor
+AR=10;//aspect ratio
+a=4;//angle of attack in degree
+//for a infinite wing of NACA-23012 airfoil:
+Clo=1.2;//lift coefficient at 10 degree angle of attack
+Cl1=0.14;//lift coefficient at 0 degree angle of attack
+ao=(Clo-Cl1)/10 //infinite wing slope per degree
+a1=ao/(1+57.3*ao/(3.14*e*AR)) //lift slope for finite wing
+a2=-1.5;//angle of attack at zero lift from standard data
+cd=0.006;//profile drag coefficient estimated from aerodynamic data
+