Helicopter Rotor Lift Equation

[Flabbyflab]

Hello!

I am creating, or at least attempting to create, a human-powered helicopter. I need an equation to figure out the lift from the rotors. I plan to use four counter-rotating rotors, three blades each, and each blade made of foam, with aluminum ribbing. The blades will be six feet each. Any other general information that might help would be greatly appreciated. Thanks!

 

[Mech_Engineer]

Hello!

I am creating, or at least attempting to create, a human-powered helicopter. I need an equation to figure out the lift from the rotors. I plan to use four counter-rotating rotors, three blades each, and each blade made of foam, with aluminum ribbing. The blades will be six feet each. Any other general information that might help would be greatly appreciated. Thanks!

You're going to need to know the airfoil profile to calculate an estimate of the expected lift:

http://en.wikipedia.org/wiki/Lift_(force )

 

[jaguar7]

The problem is that the "airfoil's " of a helicopter aka the propellor blades' motion through the air actually changes the air pressure by an amount not described anywhere that I can personally find on the internet, yet.

I have the same question as the OP.

 

[Bobbywhy]

Whenever I find someone trying to design and test an experimental system I immediately search for examples of others who have already worked on the same type of system. By studying their work and results the repetition of many of their trials and errors can be avoided. And the successful schemes they discovered may be adopted to your new project. In case you have not yet done so please see:

http://en.wikipedia.org/wiki/Human-powered_helicopter

“The current world record for human-powered helicopters is held by a craft named Yuri I, built by a team from the Nihon Aero Student Group (NASG).”

http://www.humanpoweredhelicopters.org/yuri1/index.htm

afterthought: By the way, in the helicopter world they are not called "propeller blades". The accepted term is "rotary wing".

 

[alphy]

Hello! I can provide you with the Helicopter Rotor Lift Equation, also known as the Blade Element Theory. This equation takes into account various factors such as rotor speed, blade angle, and air density to calculate the lift generated by your rotor system.

The equation is as follows: Lift = (1/2) * Air Density * Rotor Area * Blade Lift Coefficient * Blade Angle * Rotor Speed^2

In order to obtain accurate results, you will need to determine the values for each variable based on your specific helicopter design. The rotor area can be calculated by multiplying the blade length by the diameter of rotation. The blade lift coefficient can be determined through experimentation or analysis of similar blade designs.

Other factors that may affect the lift generated by your rotor system include the weight of the helicopter, the angle of attack of the blades, and the overall aerodynamics of the helicopter. It is important to consider and account for these factors in your design to ensure optimal lift and flight.

I hope this information helps in your project. Best of luck with your human-powered helicopter!