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+//consider the wing-body-tail wind tunnel model of example 7.4.
+a=0.08;//lift slope
+S=0.1;//area of wing(m^2)
+c=0.1;//chord of wing(m)
+lt=0.17;//distance between airplane'scenter of gravity and aerodynamic center of tail
+St=0.02;//tail area(m^2)
+It=2.7;//tail settling area(degree)
+at=0.1;//tail lift slope per degree
+eo=0;//downwash angle at zero lift
+de=0.35;//derivative of downwash angle w.r.t angle of attack
+Vh=lt*St/(c*S)//tail volume ratio
+Cmac=-0.032;//moment coefficient about the aerodynamic center
+//derivative of Cmcg w.r.t absolute angle of attack:
+DCmcg=a*(dh-Vh*at*(1-de)/a)
+//value of moment coefficient at zero absolute angle of attack Cmo:
+Cmo=Cmac+Vh*at*(It+eo)
+//equilibrium angle of attack(from moment coefficient curve):
+Ae=Cmo/0.0133
+\ No newline at end of file