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+//consider the same wing configuration as that of example 5.1.
+L=700; //Lift per unit span
+V=50; // velocity of flow in test section(m/s)
+D=1.225;//standard sea level density,Kg/m^3
+q=D*V^2/2  //dynamic pressure,N/m^2
+S=1.3;//wing area,m^2
+Cl=L/(q*S) //coefficient of lift
+//from the value of Cl and wing configuration we can get angle of attack by using standard table:
+a=1 //angle of attack in degree
+//To cause zero lift Cl=0,so from standard table of Cl and Lift:
+a1=-2.2 //angle of attack in degree
+\ No newline at end of file