This channel is dedicated to radio controlled model aircraft, especially the electric model airplanes. As an enthusiast on the construction from scratch of polyurethane foam models, I show the models that I have built, as well as the techniques that I have developed. I also show some calculation methods I have learned or are my own.
Este canal esta dedicado al aeromodelismo de aviones a radio control, especialmente al aeromodelismo electrico. Como entusiasta de la construcción desde cero de modelos en espuma de poliuretano, muestro los modelos que he construido, así como las técnicas que he desarrollado. También muestro algunos métodos de calculo que he aprendido o son de mi autoria
The Best of. thx for explaining. I am trying to find out why my model does not fly properly. We will see what happens when I applied information from your video
Hi there. Except for table 1, all other tables are from my own test on the test bank shown in the video (1:55) . As a Mechanical Engineer and Aeromodeller, I wanted to contribute to the hobby.
Thank you, I was a bit confused about the motor size and kv for 10x5E APC propeller, due to this amazing video i have pinned down the required kv i.e 900-1100 kv , i just need to find a suitable motor size for the above propeller . Thank you so much for the help
Queria pedirle informacion o mas bien ayuda para la distancia entre el borde de ataque del ala y el estabilizador horizontal. He visto viseos pero queria recurrir a sus conocimientos
La distancia L entre el centro de gravedad del ala (CG, aproximadamente a 30% del borde de ataque de la cuerda media aerodinamica* ) y el CG del estabilizador, (a 30% del borde de ataque del estabilizador) esta dada por el producto del area del estabilizador (AE) por L. Asi mas grande AE mas pequeño puede ser L y viceversa. L depende del tipo de avion: Trainer, Acrobatico, Cargo, etc. Como referencia, para trainer, el area del estabilizador es como 25 % del area del ala principal. * Cuerda Media Aerodinamica (CMA) = (cuerda base del ala + cuerda punta del ala) / 2 Si es un ala rectangular, pues CMA es la misma para toda el ala. Este video puede serte util: ru-vid.com/video/%D0%B2%D0%B8%D0%B4%D0%B5%D0%BE-M7ou4PJWbEY.html
Hello - hoping you can help. I have a Great Planes Kunai glider with a balsa tail. I managed to snap off one side of the horizontal stabilizer. Ive glued it back on, bit would like to reinforce somehow. It is a thin profile - so i dont rhink i could add a carbon rod. Do you have any suggestions, please?
As a newbie, everything seems so interdependent on each other that I spent hours trying to find a way out of this catch-22. I love your experimental values tables, they make choosing waay easier. Thank you!!
I’ve made a plane with a C value of about 11 and it flew but it was so hard to control that I crashed it multiple times. I’ve made a new design with a C value of around 6. I’ll reply with my findings on how much easier (if at all) it is to fly
Hi Mojar. Sorry, it is a scratch built model and I did not formal files. Here is the building process: ru-vid.com/video/%D0%B2%D0%B8%D0%B4%D0%B5%D0%BE-a90j_LL21s4.html You can find the 3 views of the plane in www.skybrary.aero/aircraft/p180
Hi Mel. The required area has to do basically with the wing load, but the airfoil has a lot to do with the type of flight. If you have a trainer or a jet, the airfoil of course is different. Also, the airfoil has to do with the drag. Thicker the airfoil, grater the drag,
Thanks for asking. Using the formula to determine the surface needed for a load, how does thrust/airfoil/drag factor into something that flies given the determined surface/weight result? It seems to me (aeronautical ignorance here) that to achieve any degree of lift, the wing profile and thrust must factor into actual flight. For example, I have a given load (70g) and a given motor (35g thrust). How is the surface needed to carry 70g related to a design that has 35g thrust? Does surface area change based on thrust?
@@melristau If you my video on How to choose a motor: ru-vid.com/video/%D0%B2%D0%B8%D0%B4%D0%B5%D0%BE-EL1vt9ufEcE.html There is a table at the beginning that relates the thrust/weight ratio according with different types of airplanes. This table is of common use by aero-modelers. There I propose a process to select a motor and propeller that has proven to be useful for the hobby. It took to me a considerable time to understand the relationship between all this variables and to put in few words all the information. Hope it will be useful for you too. I am not an aeronautical engineer, but a mechanical engineer trying to put some of what I have learned by experience in the hobby.
Thanks! Did watch. The plane I’m trying to design is based on an RC system with max thrust of only 35g! + a total load of about 70g. The lift area is what I’m experimenting with. 🙈
A bit confusing in Table (1). For RPM = KV * V ? For Power(W) = Max.V * Amp(A) ? But I found the figures in RPM and Power are not according to above formulas. Is the RPM and Power are measured figures or calculated figures ?
Hi Thar. Kv is expressed as rpm/volt, so multiplyng Kv * volts gives RPM. Same for Power. W=A*V . Data in table was obtained from manufacturers, but this data is only referential. As you see in the video calculation does not use this data.
Hi, I have a 40 size and a 60 size p51 mustang and I've been struggling to get the glow engines to work properly and I'm OVER IT!!!! I will be converting them as soon as I figure out the right combo!!!!! Both planes have never been flown and I've had both for two years!!!
Absolutely fantastic, Victor. I too have been struggling, being a newbie, to work out sizes for my rc Guillows conversions. Now I have a much better understanding. Great job
Hello Paul. Sorry for the delay. ASE is the calculation of lifting area to the power 1.5. I made tables of ASE so you do not have to calculate it. It facilitates the other calculations as explained in the presentation.
Hello; Your videos are very good,but I still don;t know how to calculate the power of 1.5 with wing loads and weight,,,can you explain how to use it...its me,I have a hard head to learn new things.............
Hello Paul. You don't need to calculate it because is already calculated and tabulated in the presentation. C= total weight/(Lifting Area)^1.5 to facilitate the calculation I call ASE =(lifting area)^1.5 , so if you have the area , you look in the table and find ASE . Once you have ASE calculate C and see what value you obtain. (less that 12 is OK) On the other hand, if you can go the other way, if you want a defined value of C (say 9, for example) you can calculate what area do you need in your model. Once you have the area, you can determine the wing according with the type of selected wing.
If you could get a real voice and maybe use cm³ (I know it's not the standard unit but it's something more commonly understood) Otherwise brilliant info.
