Aerowerx
Well-Known Member
There seems to be renewed (or continued) interest in flying wings and different lift distributions, indicated by renewal of some old threads.
This got me thinking about it again myself, and I think I am beginning to see how to achieve a BSLD. But there are a few things I would like to have clarified, just to be sure.
On the Nurflugel.com web page, they have a brief paper by R. Stadler.
These are two of the equations:
First line: In the denominator inside the braces, is that the section lift (that is, cl from 2d airfoil data) times the local chord? What angle of attack do you use for this value? Just to the right of the =, is that the cl and chord at the root?
Second line: In front of the braces, is cL the coefficient of lift for the entire wing, with A being the area? Inside the braces in the denominator, how does that cl differ from cl in the first line?
This got me thinking about it again myself, and I think I am beginning to see how to achieve a BSLD. But there are a few things I would like to have clarified, just to be sure.
On the Nurflugel.com web page, they have a brief paper by R. Stadler.
These are two of the equations:
First line: In the denominator inside the braces, is that the section lift (that is, cl from 2d airfoil data) times the local chord? What angle of attack do you use for this value? Just to the right of the =, is that the cl and chord at the root?
Second line: In front of the braces, is cL the coefficient of lift for the entire wing, with A being the area? Inside the braces in the denominator, how does that cl differ from cl in the first line?
