Ahelicopter is hovering in a steady cross wind at a gross weight of 3,000lb. the helicopter has 275 hp delivered to the main rotor shaft. the tail rotor radius is 2.3 ft and has an induced power factor of 1.15. the tail rotor is located 15.3 ft away from the main rotor shaft. determine the crosswind conditions (velocity and direction) in which tail rotor effectiveness may be reduced or lost. if the center of gravity is assumed to lie on the rotor shaft axis, determine the feasible yawing angular velocity that the pilot can demand that may also result in a loss of tail rotor effectiveness