Recent content by Jeffsg605

From my understanding, the Coefficient of Lift is a function of angle of attack and camber of the wing. It is not dependent on velocity. CL probably does change along the length of the rotor but I think I can assume it is constant for a fairly decent calculation. jack action: This is a site...

JBA, that's a really good point. I guess I wasn't sure what to use for velocity since the velocity changes depending on where you're measuring on the rotor. The original equation is taken from the lift equation for an airplane with a fixed wing so the velocity at each point along the wing is...

That's awesome, thank you so much! One thing I was bad at college was setting up the equations. I could usually solve them when they were given but I had trouble setting them up for things like this. Your answer makes a lot of sense. Thanks again!

This is noted in the Notation List on page xii where he says. A = area of rotor disc and blade area is given on the next line as Ab = total blade area (N blades) Then in chapter 2, page 15 about half way down, he states the equation for drag in autorotation as D=(1/2) p Vc2 A CD

According to J. Seddon, Basic Helicopter Aerodynamics, (link) "S is the disc area". Not saying you're wrong but I have compelling evidence that says otherwise. In any case, that still doesn't solve my unit problem.

I am trying to calculate the lift generate by a helicopter rotor using the lift equation, which is L = \frac{1}{2} \rho V^2 * C_L * S \\ where \\ \rho\mbox{ = density} \\ V\mbox{ = velocity of a point on the rotor} \\ C_L\mbox{ = lift coefficient} \\ S\mbox{ = surface area swept out by the...