aerodynamics:couple about cg.

x/t=0,25*c*cl*s(profile)
x/t=sum(r,t)0,25*c*cl*s(wing)
x/t=-(sum(r,t)0,25*c*cl*s)+arm*thrust tail=0+drag(whole plane)
1/2m*v^2+m*g*h=equilibrium:n(nis even)*arm*sum(1,infinity)*forces/g

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