Physics question - Finite wings
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Physics question - Finite wings
Posted this on the other side, but thought I would ask here also..
Hi all,
Quick question possibly for the Aerodynamic engineers amongst you.
Can anyone explain simply to me how to modify cL for finite wings. I have been making a flight simulator loosely based on blade element theory - to cement the flight physics in my head. Works amazingly well but I am currently just using the 2d wing equations and it's bugging me that this obviously doesn't account for tip vorticies.
Maths isn't my strongest point, I have figured out the linear algebra as I've gone along to get to where I am at, but pages of equations are like another language to me so struggling to get my head around it.
I understand that there seem to be different approximations for low/high aspect ratio wings and also swept wings introduce a whole extra level of complexity. What I don't get however Is what the final equations should look like.
I found the following approximation..
cl3d = cla ( ar / ( ar+2) ) a
But I think this might just be for elliptical wings?
Anyone able to offer some help without exploding my brain with complex maths?
Thankyou
Hi all,
Quick question possibly for the Aerodynamic engineers amongst you.
Can anyone explain simply to me how to modify cL for finite wings. I have been making a flight simulator loosely based on blade element theory - to cement the flight physics in my head. Works amazingly well but I am currently just using the 2d wing equations and it's bugging me that this obviously doesn't account for tip vorticies.
Maths isn't my strongest point, I have figured out the linear algebra as I've gone along to get to where I am at, but pages of equations are like another language to me so struggling to get my head around it.
I understand that there seem to be different approximations for low/high aspect ratio wings and also swept wings introduce a whole extra level of complexity. What I don't get however Is what the final equations should look like.
I found the following approximation..
cl3d = cla ( ar / ( ar+2) ) a
But I think this might just be for elliptical wings?
Anyone able to offer some help without exploding my brain with complex maths?
Thankyou
