Calculating Lift Capacity of Rotor Blades

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Discussion Overview

The discussion revolves around calculating the lift capacity of rotor blades in helicopters and similar flying devices. Participants explore various factors that influence lift calculations, including engine power, rotor blade characteristics, and environmental conditions.

Discussion Character

  • Exploratory
  • Technical explanation
  • Conceptual clarification
  • Debate/contested

Main Points Raised

  • One participant suggests that RPM, blade size, and angle are essential for lift calculations.
  • Another participant emphasizes the importance of engine horsepower as a primary factor in determining lift capacity.
  • It is proposed that the collective and cyclic pitch of variable pitch blades affects lift and engine performance.
  • A participant notes that calculating lift is complicated by structural limits of the aircraft and varying conditions such as elevation and temperature.
  • There is mention of the need for performance charts in aircraft operator's manuals to understand lift capabilities under different conditions.

Areas of Agreement / Disagreement

Participants express differing views on the factors that should be prioritized in lift calculations, indicating that multiple competing perspectives exist without a clear consensus.

Contextual Notes

Limitations include the complexity of real-world factors affecting lift, such as environmental conditions and structural constraints, which are not easily encapsulated in a single calculation.

Who May Find This Useful

This discussion may be of interest to those studying aerodynamics, helicopter design, or anyone involved in aviation engineering and performance analysis.

bobo67
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What calculation is the to find the amount a helicopter (or flying device using rotor blades) can lift? I would of thought I would need to take into consideration the RPM of the blades, the size of the blades and maybe the angle. I was hoping there would be some calculation telling me how much it can lift.
Thanks
 
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I would think the first consideration of "can lift calculations" would be engine horsepower or equivalent units.

Once you know what the engine puts out, you can figure how to transfer it to thrust. Almost all helecopters have variable pitch blades, for lift you could say the collective pitch verses cyclic.(think of the variable pitch blades as your adjustable transmission, (too much pitch too much work trying to be done), and the engine bogs down and strays from optimal power output.

Most turbine helecopters set the engine to a "set" optimal RPM. From this set RPM, you adjust the pitch of the blades.

Loooonnngg story short, find the engine horsepower and calculate lift from that, (after you subtract the weight of the helecopter). Because of induced drag losses on the rotor blades, etc,etc,etc,etc, I would guess less than 75% of what the engine(s) put out is available for lift.
 
There is no straightforward calculation because the real world numbers take into account a lot more factors than just the engine max power and the blade lift. There are a lot of other limiting factors like structural limits on the fuselage and the blades/rotor hub them selves which may limit the max lift available. There's also the issue of whether in a hover or in forward flight, etc...

Not to mention that all things change at different elevations and temperatures and humidity. That is why a very large section of most aircraft operator's manuals have charts on allowable performance at certain conditions. If you're looking to look at a real aircraft, look in it's operator's manual. Any number you calculate won't be in the ball park.
 
Thanks very much for your help. It made it a lot clearer.
Thanks
 

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