I am trying to draw a span lift distribution chart but my maths knowledge is too rusty these days (currently trying to revise it).
"Theory of wing sections" page 22 gives a formula to calculate the effective angle of attack for a wing section but I am unable to extract a value from it:tired:.
Could anyone please explain to me how I am supposed to use it.
αe=f(Cl)=α - 180/π*b/π∫((d/dy)(Clc/4b)dy)/(y1-y)
Perhaps a bit hard to read hewe at the forum but it is equation 1.10 on page 22 in the book.
Thanks for your help!
"Theory of wing sections" page 22 gives a formula to calculate the effective angle of attack for a wing section but I am unable to extract a value from it:tired:.
Could anyone please explain to me how I am supposed to use it.
αe=f(Cl)=α - 180/π*b/π∫((d/dy)(Clc/4b)dy)/(y1-y)
Perhaps a bit hard to read hewe at the forum but it is equation 1.10 on page 22 in the book.
Thanks for your help!
