Relation between lift force and torque produced in propeller used for vertical take-off and landing aircrafts There are many answers for this question but none of them are specific.
I need to find the exact relation between the lift force of a propeller of specific pitch, attack angle , dimensions and material with torque to be produced in a propeller at a specific speed at a certain altitude of a vertical take-off and landing aircraft to hover and fly forward.
Can some experts in the field derive this relation.
The relationship of torque produced by the engine and lift force will be the drag of the rotor.  Increase in lift force by increasing rpm or AOA will require a proportional increase in power output from the engine.  Air density also plays a role.
With a common helicopter, torque is counter balanced by increasing or decreasing torque of the tail rotor.