- #1
perrabananskruv
- 3
- 0
is the formula below valid to calculate the lift coefficient for a delta wing?
Cl=2*L/(rho*v^2*A)
L=lift (N)
rho= air density
v= air velocity
A=wing area
im doing a subsonic wind tunnel project where I am going to measure the lift for a low aspect ratio delta wing. should i use another theory to calculate the lift?
Cl=2*L/(rho*v^2*A)
L=lift (N)
rho= air density
v= air velocity
A=wing area
im doing a subsonic wind tunnel project where I am going to measure the lift for a low aspect ratio delta wing. should i use another theory to calculate the lift?