# How much lift must a helicopter rotor produce?

How much lift must a typical helicopter rotor produce? For example, consider the rotor of what seems to be a common helicopter: the Robinson R22. Is the lift produced equal to one of the following:

• The weight of the helicopter;
• Double the weight of the helicopter; or
• Simply some value greater than the weight of the helicopter?

For example: for a 700kg helicopter, what maximum lift will the helicopter rotor need to produce?

• In order for it to fly, it has to produce more lift than weight... Commented May 16, 2017 at 18:22
• This may be a little too broad. Depends on the phase of flight. In a hover (ignoring ground effect and some other factors), the lift produced must exactly equal the weight of the craft. For a climb, the lift produced must be greater, how much so depends on how fast you want to climb. Conversely, to descend, lift should be less than weight, again the extent depends on how fast you want to go down... Commented May 16, 2017 at 20:48
• This may be better suited for physics.se Commented May 17, 2017 at 5:43
• The QE already knows that the (maximum) weight of the helicopter must be lifted. Now, the question is what is the minimum required vertical acceleration performance, and what margins are required. What other parameters play a role, max. service altitude, etc. ? The question is not that broad.
– bogl
Commented May 17, 2017 at 7:47
• My answer was wrong, because I forgot a simple concept which is that the initial force required would be more (from rest, to lift the craft) that it would be to further lift the craft. Commented May 17, 2017 at 8:18