http://www.starlino.com/power2thrust.html

*by Sergiu Baluta, Starlino Electronics, revised 10/30/2015*

This article is a theoretical venture that aims to answer a series of practical questions, such as:

– given a certain electrical setup that can generate a certain power, what is the maximum thrust that we can achieve ?

– can a human-powered aircraft be built ?

– can I tell the expected thrust generated by a copter simply by knowing the power it consumes and vice-versa ?

– are larger propellers really more “efficient” ?

– which multicopter configuration is more efficient: tricopter , quadcopter , hexacopter or octacopter ?

– I heard that for every gram of mass I add to my multicopter, the flight time will decrease by 1 second, can you put any sense in this ?

*– and many more…*

When selecting motors for an RC model you will often come across the thrust tables that tell you how much thrust (or “pull”) a specific motor can generate. This usually depends on few factors: the propeller used and the voltage applied. Next to these two parameters you will usually see the current and power consumed and the resulting thrust generated, usually expressed in grams. If you want your model to hover, you must ensure that your motors can generate a thrust equal to or greater than the mass of the model.

The power that your motor consumes is calculated based on the simple formula:

**P = V * I** , where V is the voltage and I is the current.

Power represents the amount of energy we’re consuming per second, which is expressed as follows:

**P = E / t**, where E is the energy.

The efficiency of a specific setup consisting of a propeller and a motor is often calculated as:

**Eff = Thr / P** , where **Thr** is the thrust force generated expressed in grams and **P **is the power consumed expressed in Watts.

However this efficiency is not expressed in percentage as you would usually expect so it does not tell us if our motor-propeller setup is consuming energy exclusively to generate lift or wasting it somewhere else. To compute an efficiency value in percentage we would need to know the minimum or “ideal” power necessary to generate a specific thrust given our setup and environment.

We have to mention from the start that such an “ideal” model, taking into account all the possible factors would probably be too complex to use for practical purposes. So instead our goal is to first deduct and then define a “theoretical” or “reference” power formula. Finally this formula will be applied to a series of practical experiments and the resulting “theoretical” power will be compared to the real-world observed power. To avoid confusion with the other efficiency let’s call this ratio “Theoretical Thrust Ratio” or **TTR**:

**TTR = P(real) / P(theoretical)**

So let’s dive into our calculations. But before we do that, for the impatient reader, here are the formulas that we’ll be deducting and using for computing our “theoretical” power (or thrust – if we flip the formula around):

Here **P **is the power expressed in **W**atts., **F **is the thrust expressed in **N**ewtons, **r** is the radius of the propeller expressed in **meters **and **K** is a air density dependent coefficient, with a nominal value of **0.3636** assuming air pressure of **1atm** and air temperature of **20C**.

The formulas above are expressed in international physical units, however for those doing RC I am also providing the following convenient formula for computing thrust in grams **Tgram**, based on a propeller diameter expressed in inches **Dinch**:

Here **C **is an air density dependent coefficient with a nominal value of **0.0278 **assuming air pressure of **1atm**and air temperature of **20C**.

Below is a lookup table for K and C coefficients at various temperatures and air pressure of 1atm.

Temperature (degrees C) | Air Density (kg/m^3) @ 1atm | K | C |

35 | 1.1455 | 0.372745594 | 0.02850295 |

30 | 1.1644 | 0.369708101 | 0.02827068 |

25 | 1.1839 | 0.366650731 | 0.028036891 |

20 | 1.2041 | 0.363562254 | 0.027800722 |

15 | 1.225 | 0.360447503 | 0.027562545 |

10 | 1.2466 | 0.357311097 | 0.027322712 |

5 | 1.269 | 0.354143483 | 0.027080492 |

0 | 1.2922 | 0.35094996 | 0.026836291 |

?5 | 1.3163 | 0.347722365 | 0.026589484 |

?10 | 1.3413 | 0.344466588 | 0.026340523 |

?15 | 1.3673 | 0.341175753 | 0.026088881 |

?20 | 1.3943 | 0.337856246 | 0.025835046 |

?25 | 1.4224 | 0.334502366 | 0.025578583 |

Let’s get back to the main question of this article – *“how much power is needed to hover an object ?” ,* or in other words how much energy we need to consume per second to maintain this object “in the air”. Well, as it turns out “it all depends…”. For example we do not need to consume any energy to keep a book on a shelf or a tire suspended on a rope. Clearly we did not formulated our question correctly! So let’s try again and this time be more specific. “How much power does a craft powered by a spinning propeller needs in order to hover in the air ?” Here you go – much better ! Let’s see if we can answer this question.

You might recall from school physics a rule called “preservation of energy”, it simply states that the energy does not like to go away or disappear, all it does – it transforms from one form to another. We certainly know that our craft consumes energy in the form of electricity or burned fuel, but where does it go ? Didn’t we say that we don’t need energy to hover an object such as a book on a shelf or a tire hanging on a rope ? The reality is that not every object is as lucky as a book on a shelf or a tire suspended on a rope. In both these cases – the book and the tire have the benefit of a “reaction force” of the shelf and rope respectively. The book pushes on the shelf with its weight and the shelf will always push back with an equal force in the opposite direction. If you’re confused it’s probably because of a common misconception that an existence of a “force” implies that energy is consumed. The later is not true – a “force” can exist simply because of the setup of the nature, for example the gravitational force, the magnetic force and the reactive force they all simply exists without consuming energy. It’s their action that might or might not lead to the transfer of energy.

Back to our model of a propeller-powered craft, since our craft is suspended in the air, there must clearly exist an opposing force **F **that is directed in a opposite direction:

**F = m * g** , where **m** is the mass of our craft and **g** is the **acceleration of gravity (** approximately 9.8 m / s^2 ).

In fact this force is not much different from the “reaction force” that a shelf exerts on the book, except our medium “the air” is less dense than the shelf and as a result of this force, as we push “against” it with the propeller, the air starts moving. Here you go! We found were our energy goes.** The electrical or fuel energy consumed by an aircraft is transferred to the kinetic energy of the moving air.**

Let’s imagine a spinning rotor that generates a thrust **F** (in case of hover it is equal to **mg**) and a cylinder of air of infinite height with the rotor placed in the middle. The rotor is sucking air from the top and then pushing it down from the bottom. The rotor will have very little influence on the air on the top (since it’s very-very far away) so we can assume the speed of the air starts at 0, then slowly increases as it passes the rotor to **w/2** (due to symmetry of our model from top and bottom) and finally as it reaches the bottom of the cylinder it stabilizes at a speed **w**,** **again rotor has very small influence on the air from the bottom of cylinder since it’s far-far away.

Let’s examine our model for a period of time **t **that it takes for a particle of air to travel from the top to bottom of cylinder** . **Let’s note the area of the cross-section of our cylinder as **A **and since it’s defined by the radius of our rotor we have:

The volume of air **Vol** that passes through the rotor during the time **t**, can be calculated by monitoring how much “height” of air passes through the rotor at the speed **v, h=v*t **and multiplying by the cross section area **A.**

Given the air density **Qair **we can calculate the mass of air that passes through the rotor in the time period** t**:

Let’s note that since the air starts at zero speed so its starting momentum is zero, thus it’s momentum change will be equal to final momentum **Mair * w**, where **w **is the final speed. From momentum conservation theory we can recall that the force that we apply on a mass is equal to the rate of change of momentum:

Finally combining the last two formulas we get:

From here we can get the speed **v **at the rotor**:**

Next let’s note that the power consumed is equal to the work done by the force **F **at the rotor (work and power are both defined by the rate of change of energy), which is given by another classical formula **W=F*v**:

Note that we substituted the circle area **A = PI*r^2 **formula. Finally, by extracting some coefficients we get:

and the inverse formula for thrust is:

The formulas above work with international physics units, thrust **F **is measured in **N**ewtons, and radius **r** is measured in **m**eters. For practical purposes in **RC **we work with propeller diameter in inches and thrust is calculated in grams (which is equivalent to mass this thrust force can hover from **F = mg** formula, where **g **is standard gravity ~ 9.8m/s^2). So let’s define another equivalent set of formulas:

and the inverse formula is

To verify these theoretical results I conducted a series of thrust tests using different motors and propellers commonly used in RC. Also I verified thrust tables randomly found on the internet (forums or motor specs):

**Motor**: DYS 1306 3100KV BX **Source**: http://www.banggood.com/DYS-1306-3100KV-BX-Series-Brushless-Motor-For-Multicopter-CW-CCW-p-962149.html

Prop Diam " | Prop Ptich | V | A | Thrust(g) | W | Eff (g/W) | Theoretical Thrust (g) | TTR=Thrust /Theoretical Thrust |

5 | 3 | 7.4 | 1.4 | 70 | 10.36 | 6.8 | 151 | 46.2% |

5 | 3 | 7.4 | 3.3 | 140 | 24.42 | 5.7 | 268 | 52.2% |

5 | 3 | 7.4 | 5.7 | 220 | 42.18 | 5.2 | 386 | 57.0% |

5 | 3 | 11.1 | 2.1 | 100 | 23.31 | 4.3 | 260 | 38.5% |

5 | 3 | 11.1 | 5.5 | 210 | 61.05 | 3.4 | 494 | 42.5% |

5 | 3 | 11.1 | 9.4 | 350 | 104.34 | 3.4 | 706 | 49.6% |

6 | 2 | 7.4 | 1.3 | 70 | 9.62 | 7.3 | 163 | 43.0% |

6 | 2 | 7.4 | 3.7 | 150 | 27.38 | 5.5 | 327 | 45.9% |

6 | 2 | 7.4 | 7.9 | 230 | 58.46 | 3.9 | 542 | 42.4% |

**Motor:** EMAX MT1804 2480KV **Source**: http://www.rcgroups.com/forums/showthread.php?t=2172324

Prop Diam " | Prop Ptich | V | A | Thrust(g) | W | Eff (g/W) | Theoretical Thrust (g) | TTR=Thrust /Theoretical Thrust |

5 | 3 | 12.1 | 7.3 | 345 | 88.33 | 3.9 | 632 | 54.6% |

5 | 3 | 12.2 | 6.2 | 330 | 75.64 | 4.4 | 570 | 57.9% |

5 | 4 | 12.1 | 9 | 370 | 108.9 | 3.4 | 727 | 50.9% |

6 | 3 | 12.2 | 8.6 | 410 | 104.92 | 3.9 | 800 | 51.2% |

**Motor:** DYS BE1806 2300KV

Prop Diam " | Prop Ptich | V | A | Thrust(g) | W | Eff (g/W) | Theoretical Thrust (g) | TTR=Thrust /Theoretical Thrust |

5 | 3 | 12 | 9 | 415 | 108 | 3.8 | 723 | 57.4% |

5 | 3 | 12.2 | 3.6 | 230 | 43.92 | 5.2 | 397 | 58.0% |

5 | 3 | 12.1 | 7.5 | 360 | 90.75 | 4.0 | 643 | 55.9% |

5 | 3 | 12.2 | 3.3 | 205 | 40.26 | 5.1 | 374 | 54.8% |

5 | 4 | 12 | 10.6 | 440 | 127.2 | 3.5 | 806 | 54.6% |

5 | 4 | 12.1 | 4.2 | 225 | 50.82 | 4.4 | 437 | 51.5% |

6 | 3 | 12 | 10.2 | 485 | 122.4 | 4.0 | 887 | 54.7% |

6 | 3 | 12.1 | 4 | 240 | 48.4 | 5.0 | 478 | 50.2% |

6 | 4.5 | 11.8 | 16.1 | 580 | 189.98 | 3.1 | 1189 | 48.8% |

6 | 4.5 | 12 | 5.1 | 235 | 61.2 | 3.8 | 559 | 42.1% |

5 | 3 | 16.3 | 11.5 | 570 | 187.45 | 3.0 | 1044 | 54.6% |

5 | 3 | 16.4 | 5.1 | 280 | 83.64 | 3.3 | 609 | 45.9% |

A more extensive list of test can be downloaded here, the Excel Spreadsheet contains a _TEMPLATE_ sheet that you can use to fill in and verify your own data:

http://starlino.com/wp-content/uploads/data/power_thrust/Motor_Thrust_Tests.xlsx

A:A trained cyclist can generate 500W peak power (or even 1500W according to some reports), let’s a assume the cyclist weights 70Kg and the weight of the copter is 30Kg, thus the thrust needed for lift off is 100Kg. From this formula:

we can compute the radius of the propeller that this human-powered helicopter will need to have :

r = K * (mg) ^ (3/2) / P = 0.3636 * (100*9.8) ^ (3/2) / 500 = 22.3 (meters)In fact human powered machines have been built. Let’s analyze for example the Gamera II built by University of Maryland:

Weight: ~37kg + Pilot ~ 90kgRotors Radius:~ 7.2m ( x 4)Since this craft has 4 rotors , each rotor would need to produce at least 1/4 of the thrust or 90Kg / 4 = 22.5Kg . Using our formula we can calculate power needed for each rotor:

P = K * (mg) ^ (3/2) / r = 0.3636 * (22.5*9.8) ^ (3/2) / 7.2 = 165.35

Thus the total power required is estimated at 165.35W*4 =

661.4 W, which is quite manageable for a trained cyclist. In reality no motor is 100% efficient. Still, an advantageous effect for take-off is the “ground effect”. As air is pushed into the ground its density increases, as a result ourKcoefficient will decrease, meaning there’s less power required to generate same thrust compared to less dense air.

A:Simply apply this formula to get the thrust in grams:

Tgrams = ( P * Dinch / C) ^ (2/3) = ( 200 * 10 / 0.0278) ^ (2/3) =~ 1730 gram, gram/Watt efficiency immediately follows: Eff = 1730 / 200 = 8.65. From practice, knowing that most brushless motors setup used in RC will deliver 50-60% of theoretical thrust and efficiency you can divide the above theoretical values by 2 to get a real-life estimate , so P ~ 865g, Eff ~ 4.3 g/ W.

**revised 10/30/2015**

*by Sergiu Baluta, Starlino Electronics*

评论这张

<#--最新日志，群博日志-->
<#--推荐日志-->
<#--引用记录-->
<#--博主推荐-->
<#--随机阅读-->
<#--首页推荐-->
<#--历史上的今天-->
<#--被推荐日志-->
<#--上一篇，下一篇-->
<#-- 热度 -->
<#-- 网易新闻广告 -->
<#--右边模块结构-->
<#--评论模块结构-->
<#--引用模块结构-->
<#--博主发起的投票-->

## 2 COMMENTS | Add Comment | RSS

1.starlino | October 30, 2015Please note that on 10/30/2015 I revised completely this article and calculations. Thanks to Olli and others who pointed out ways to improve it, your input is much appreciated ! In order not to confuse future readers I removed the comments that where related to old article. Thank you !

2.Yuri | October 31, 2015Thank you very much for very clear explanations and broad set of data. There may be some logical extension to your analysis. You include prop pitch values, but its effect on overall picture is only in actual motor power consumption, so it is not needed for your analysis. But it is very important for copter agility and the health of its elecrtic system. If you use 2212 2600kv motor with 6" prop with 4.5" pitch it will generate about 700 to 900 g thrust, but even 30A ESC will be very hot and there is a potential to catch fire (I have seen how ESC burst in flames). The use of 3" pitch prop will reduce consumed power almost two times. So, there are high RPM motors with high kv-rating (but it is not ultimate parameter, the hight of rear earth magnets also plays big role), and slow, high torgue motors. It would be good to have the extension of your paper towards incorporation of prop pitch, motor kv rating and ESC amperage. Not in formal form of classical physics, but rather in the form of an estimation or approximate formula. I would be happy to help as much as I can. I have very vague undersanding of ESC principle, but their amperage rating seems to be not very trustful, and what is the amperage of 3-phase variable frequency current? Sorry for lengthy comment. I appreciate any input on raised questions.