Originally Posted by
212man
I don't know what the FAA manual says, but in reality a rotor is not demonstrating conservation of angular momentum at all! It can hardly be described as being in a zero torque, frictionless, environment!
212man Correct, Angular momentum is not applicable when there is a torque applied, however, consider the rotor system in autorotation or rapid descent (power on or off), this is when conservation of angular momentum is prevalent.
dickmct couldn't agree more
Originally Posted by
Robbiee
Its basically; When a blade flaps up, its center of mass moves inward towards the hub, causing it to accelerate. When the blade flaps down, the center of mass moves outward towards the tip, causing it to decelerate.
Fully-articulated rotors absorb this acceleration and deceleration through the lead/lag hinges. Semi-ridged rotors don't experience it to the extent that fully-articulated rotors do, as the center of mass remains virtually unchanged as the system teeters, due to the underslinging of the blades.
Robbiee correct, however the principle you are describing is conservation of angular momentum, and not Coriolis effect. Conservation of angular momentum is just one part of the formula that describes the theoretical / fictitious Corilis effect