chipmeisterc
4th Nov 2013, 17:09
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