How do I compute thrust of a rotor disk and the necessary power to drive it??

as it seems, this question has been asked a few times here so please forgive me for asking again.

If I have 50 BHP shaft power available at 5000 RPM and 106 N.m torque, then can I convert it to 200 kgf of thrust?

I intend to use two sets of horizontal rotors, dividing 50 BHP between them and each generating 100 kgf thrust. Is it doable? What will be the diameter of propellers and their RPM to achieve this goal? What about pitch?

Any help, even if in part or help in the form of guidance to correct resource will be immensely helpful.

Edit: 1. I intend to provide vertical thrust and not horizontal as we do in aircraft. 2. I want to specifically know following things:-

Suppose I have a generic 2000 mm diameter rotor blade, (I have no idea what typical pitch value is). I want to know what RPM it needs to be turned at to produce 100 Kgf force and what will be the power or torque requirement.

• You are going to lose some (or a lot) of power in the mechanism you use to divide the power between the props. Commented Nov 15, 2017 at 18:54
• What RPM will you be turning the blades at? If you're thinking 5000RPM, you'll need a very small diameter to keep the tips subsonic. If you're thinking less, then you'll need a gearbox mechanism (with losses) Commented Nov 15, 2017 at 18:56
• 5000 rpm are 523,6 rad/sec and 523,6 rad/sec x 106 N.m is 55,5 kW, around 75 hp, not 50... Commented Nov 15, 2017 at 19:42
• @xxavier yes, max torque is usually at a lower than max rpm. Commented Nov 15, 2017 at 22:28
• What is the design speed of the craft? Horizontal rotors or vertical propellers? Commented Nov 16, 2017 at 1:56

I'm answering the question of after the Edit. Simple momentum theory:

$$T = C_T \cdot \rho \cdot A \cdot \Omega^2 \cdot R^2 \tag{Thrust}$$ $$P = C_P \cdot \rho \cdot A \cdot \Omega^3 \cdot R^3 \tag{Power}$$ $$C_P = \frac{{C_T}^{3/2}}{\sqrt2} \tag{Ideal Power}$$ $$FM = \frac{Ideal Power}{InducedPower+ProfilePower} \tag{FigureOfMerit}$$

The Figure Of Merit is a dimensional unit and provides an efficiency measure. It always gives a better result for higher disk loadings, but does provide a correction for real life effects on the ideal power. So for your case of two rotors, each with: $$A = 3.14 m^2, \rho = 1.225, T = 981 N$$ the ideal power is:

$$P_{ideal} = N_{rotors} \cdot \left(\frac{(T)^{3/2}}{\sqrt{2 \cdot \rho \cdot A}}\right) = 2 \cdot \left(\frac{(981)^{3/2}}{\sqrt{2 \cdot 1.225 \cdot 3.14}} \right) = 22.2 kW$$

From J. Gordon Leishman, Principles of Helicopter Aerodynamics:

$$C_T = \frac{T}{\rho \cdot A \cdot \Omega^2 \cdot R^2} \tag{CT}$$
Tip speed $$V_{tip} = \Omega \cdot R$$ should not exceed critical Mach = 0.7 * 340 m/s = 238 m/s. At this tip speed, $$C_T$$ = (981)/(1.225 * 3.14 * 238$$^2$$) = 0.0045. Corresponding Figure of Merit = 0.55. So the power to drive both rotors would be $$22.2 kW / 0.55 = 40.3 kW$$

The rotors would turn at 238 rad/s = 2,270 rpm, hopefully that is around the rpm for max. torque for your engine. Otherwise you need to gear up/down as required, you have gearboxes anyway.

You would need to add transmission losses for driving the two rotors from your engine. Prouty gives a power loss per stage of 0.0025[max.power + actual power]. Each disk has 2 stages, so a power loss of about 0.005 * 2 * 40,283 = 0.403 kW.

$$Torque = P / \Omega = 40,685 / 238 = 170.9 Nm$$

EDIT

A numerical error in calculating $$C_T$$ = 0.0045 not 0.009, so the FM is lower and torque may not be enough. In that case the rotor diameter should be reduced and the rpm increased.

EDIT2

Clarified that Ideal power and Thrust coefficient are being calculated for two rotors/disks with half the load each. original question asked for 100kg (981N) thrust each rotor, or 200kg total. So Ideal power increases from 7.8kW to 22.2kW. $$C_T$$ was already calculated for each disk at 981N.

• This is unbelievable, I can't really thank you enough kind stranger from the internet. Now I am going to study this momentum theory and see for myself how's and why's of its application in this case. Thank you very much again :) Commented Nov 16, 2017 at 10:16
• No worries mate. The momentum theory is only the beginning, it gets head spinningly complex later in the books. But this is kind of a quick Order Of Magnitude computation. Commented Nov 16, 2017 at 10:36

Use this formula:

(From Wikipedia entry https://en.wikipedia.org/wiki/Disk_loading). Where P is the power in watts, T the thrust in Newtons, A the disk area of the rotor in sq. meters, and rho the air density in Kg/m3, around 1,22...

• I would upvote this answer if it used the equation for a worked out solution. Commented Nov 15, 2017 at 22:30
• The OP needs only to solve for A in order to know the disk area he needs, assuming 100% prop and transmission efficiency. Then he can split the area in two parts, one for each prop, and get the prop diameter. Very elementary, 12-year old algebra... Commented Nov 15, 2017 at 22:37
• Where is profile drag and induced drag in this equation? The huger the rotor disk, the lower the power required to drive it at a given thrust? Commented Nov 15, 2017 at 22:41
• It's a simplified approach based on momentum theory. Setting a convenient value for prop efficiency would take things closer to reality. Yes, in general, the larger the rotor disk, the lower the power needed for a given thrust. That's the reason helicopters have big rotors... Commented Nov 15, 2017 at 22:54
• Well if I work this out with T= 981 N, area = pi sq. mtrs, density = 1.225 kg/m^3. Then it works out to Power = 981*((981/3.14)*(1/(2*1.225)))^(1/2) = 11077 Watts, and I have 25 KW available per shaft, this looks quite promising. Assuming props are 80% efficient then it's 13.843 KW, assuming 5% mechanical losses then it's 14.572 KW. This looks magical Commented Nov 16, 2017 at 3:25