I would like to calculate the maximum windspeed in which a helicopter may safely take off and safely land, assuming a theoretical wind environment with constant wind direction and no gusts.
I understand that Effective Translational Lift is generated when taking off into the wind, which increases the climb rate.
However, I would like to understand at what windspeed taking off and landing into the wind is theoretically no longer possible for a given main rotor RPM.
Some factors I have considered include:
- while the main rotor is spinning at less than flight RPM, and nonrigid, that it may come in contact with the fuselage.
- during takeoff or landing: if the vehicle must pitch forward to compensate for extremely strong headwinds while inches above the ground, the main rotor may strike the ground
While not relevant to the theoretical wind environment described above: if there are gusts, I have also considered:
- during takeoff or landing: while hovering inches above the ground, a strong crosswind may roll the vehicle above a threshold which causes the main rotor to strike the ground.
What methods might I use to calculate these (and any other factors I have not considered) precisely?