dshively
Mechanical
- Jun 3, 2010
- 1
Hello,
I have a question regarding drag on a moving airfoil, as in a wind turbine. In the simplest form, say an airfoil is moving forward at zero angle of attack at a speed V with a tail wind of U. Is the drag:
a.) D = Cd*1/2*rho*A*(U^2-V^2)
b.) D= Cd*1/2*rho*A*(U-V)^2
Difference of the squares or square of the difference? (there are plenty assumptions in the above - one being that Cd is equal at 0 and 180 AoA, if it wasn't there would be a Cd term before each U and V).
Thank you.
I have a question regarding drag on a moving airfoil, as in a wind turbine. In the simplest form, say an airfoil is moving forward at zero angle of attack at a speed V with a tail wind of U. Is the drag:
a.) D = Cd*1/2*rho*A*(U^2-V^2)
b.) D= Cd*1/2*rho*A*(U-V)^2
Difference of the squares or square of the difference? (there are plenty assumptions in the above - one being that Cd is equal at 0 and 180 AoA, if it wasn't there would be a Cd term before each U and V).
Thank you.
