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I am looking to build an Airplane, the weight of Airplane will be around 20 to 25 kg and I am going to use a 70cc motorcycle engine as an Airplane engine.

I want to know how I can calculate the engine thrust. The 70cc engine is an air-cooled, four-stroke, single cylinder, OHC petrol engine generating a maximum power of 5.19Ps at 7500 rpm and a maximum torque of 0.519kgm at 5500 rpm.

So will it work as a plane engine or not, and can you give me any rough idea about how much thrust will it produce and how big propeller do I need for this engine.

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    $\begingroup$ Welcome to aviation.SE. You must edit the title to reflect the question. Also consider take a tour as you are a newcomer. $\endgroup$ – Manu H May 7 at 6:20
  • $\begingroup$ 3.8 kW sounds like way too little. Powered hang-gliders normally use 11 kW. $\endgroup$ – Jan Hudec May 7 at 7:12
  • $\begingroup$ Related if not a dupe: Can an ultralight aircraft fly with a 18hp engine? (it contains information needed to built such aircrafts) $\endgroup$ – Manu H May 7 at 7:55
  • $\begingroup$ Hint: Pushing double the volume of air at half the speed will require half the energy. This is why high-bypass ratio engines are better. You will have to balance this with weight and other losses that come from having a larger propeller. $\endgroup$ – Abdullah May 7 at 12:56
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    $\begingroup$ @JanHudec his airplane is almost certainly not manned at 25kg. Maybe he wants a drone? $\endgroup$ – Abdullah May 7 at 13:00
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This that follows isn't an accurate calculation, but may be useful as a starting point: let's say the mass of your plane is 23kg. That's a weight of 225 newton. You have to add 830 N for the pilot, so the total weight is 1055 N. Let's assume, also, that the best L/D of your airplane is 9 at 36 km/h = 10 m/s. In a glide, that would mean a sink speed of 10/9 = 1,11 m/s. The implied 'gravitational power' would be 1055 x 1,11 = 1171 watt. That would be the minimum power required for s/l flight at best L/D and for a 100% prop efficiency. In the real world you might need at least three times that power, around 3500 watt.

Now, concerning the relationship between prop size, power, and thrust, at 100% prop efficiency, you may use this formula for the stationary case (airspeed = 0):

enter image description here

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

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  • $\begingroup$ I would feel better assuming that the 23kg was the loaded weight of the (presumably unmanned) aircraft. The questioner did not indicate otherwise $\endgroup$ – Abdullah May 7 at 13:12
  • $\begingroup$ That's true, but the calculation can be easily repeated for any mass... $\endgroup$ – xxavier May 7 at 13:15

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