1
$\begingroup$

How would you go about finding an equation for the lift coefficient of this wing where the lift distribution is known to be elliptical but the planform is not?enter image description here

$\endgroup$
0
0
$\begingroup$

The (local) lift depends on many factors - not only the chord but also the profile, angle of incidence - and even up to the actual local flow. Without knowing the details of the actual wing, the distribution of lift can be hard to calculate.

$\endgroup$
-1
$\begingroup$

The shape of lifting lines is elliptical (viewing from the front)

$\endgroup$

Not the answer you're looking for? Browse other questions tagged or ask your own question.