A helicopter is hovering in a steady cross wind at a gross weight of $1360$ kg$.$ This helicopter

has $205$ kW power being delivered to the main rotor shaft which spins in anticlockwise

direction. The tail rotor radius is $0\mathrm{.}70$ m and has induced power factor of $1\mathrm{.}15.$ The tail

rotor is located $4\mathrm{.}66$ m from the main rotor shaft. Determine the cross wind conditions

$($wind speed and direction$)$ in which the tail rotor effetiveness may be reduced or lost.

If the center of gravity is assumed to lie on the rotor shaft axis, determine the feasible

yaw angular velocity that the pilot can demand that may also result in a loss of tail rotor

effectiveness.