Designing a Fixed Wing RC Aircraft in MATLAB Editor
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- Опубликовано: 20 авг 2024
- Here I discuss how to take some aerodynamics equations from previous videos and create a tool to design an RC Fixed wing aircraft. It's kind of a long video hope it's good. Here's the code I used in the video.
github.com/cmo...
![Broyden's Method for a vector function f([x1;x2]) = scalar](http://i.ytimg.com/vi/wT8UVzEVhvk/mqdefault.jpg)
![Broyden's Method for a vector function f([x1;x2]) = scalar](/img/tr.png)
Thank you for sharing this design methodology it has been very helpful to me. please keep making such videos professor.
@#monte_carlos
Thank you for sharing this extended screen cast. It was worth it!
And, sir, I hope you plan on doing something similar with Quadcopters in the near future.
Also, it would be great to know if Blade Element Theory for the Propeller blades may be covered as well as some Rotational/Transformation matrix if it is okay by you sir.
Thank you sir.
Quadcopter design is really more about just choosing hardware rather than any aerodynamic design. Typically places like Tiger Motors have data sheets to show how much thrust you get given the propellor, throttle setting and battery voltage. It will also tell you the current at various throttle settings so you can choose an ESC properly. Therefore there are not very many calculations other than ensuring that 4*T = W where T is thrust and W is weight.
As for BEM that would be an interesting video to make and perhaps I will do it.
@@CarlosMontalvo251 Alright. Thank you for sharing sir. I should check out Tiger motors. Also I look forward to your lecture on BE theory whenever its convenient for you sir.
excellent video sir
Can we find these parameters(CL, CD, or lift, drag) exact value in Ansys fluent analysis or Solidworks?
I couldn't find the proper resources to find this parameter in Ansys or SolidWorks.
I have been using xflr5 for a year, I find it inaccurate while analyzing wing or whole aircraft.
if u know how to do this analysis pls make a video or suggest where I can find resources
It's possible to use Ansys or Solidworks and some of my students have used it before but I myself have not. If I ever use it perhaps I will make a video. My area of expertise though is in Flight Dynamics so aerodynamics is not my specialty.
Excellent video! Thanks for sharing, I will use this in the near future in my hobby. Just a question, what about constraint diagrams? I took a course a long time ago and the professor started with those diagrams. Are they maybe overkill for RC airplanes?
I'm not sure what a constraint diagram is but it sounds like a skill learned in a senior design class. Stuff like that would be appropriate for a DBF competition or perhaps a full time job but if you're just building something for a hobby I would say that's overkill. When I design RC aircraft I usually just draw a picture, make sure my wing loading is good and then build it and put the biggest motor and battery it can take.
why we dont use alpha0_deg we convert to radian ?
alpha0_deg is the zero lift angle of attack in degrees and alpha0 is the zero lift angle of attack in radians. So I have 2 variables in the code one that is in radians and one that is in degrees.
@@CarlosMontalvo251 Huge thanks to you Mr. Carlos. At 15:30 i notice that it should be CLA = Cla/(1+(Cla/(pi*e*AR))); need to add extra parentheses
what is the cd0 cd2 difference i dont get it
The plot of drag coefficient versus angle of attack is nonlinear so aerodynamicists try and use a polynomial expansion to compute Cd (drag coefficient) as a function of angle of attack (alfa).
The formula then is
cd = cd0 + cd2 * alfa ^2
cd0 and cd2 are constant coefficients. Alfa is the independent variable and cd is the depedente variable. Cd0 and cd2 are the coeffients of the polynomial expansion.
@@CarlosMontalvo251 i get it but how can i get cd2 quantity. You chose cd0 =0,01 when the curve touch cd-axis what about cd2 you choose 0.037 ?
@@giovannigiorgio0 Cd2 needs to be obtained either through curve fitting or just by grabbing a point on the curve and solving for Cd2
@@CarlosMontalvo251 thank you Sir. If you have a full code can you share with us? Because this L/D, drag graphics etc. you deleted.
@@giovannigiorgio0 sure github.com/cmontalvo251/MATLAB/blob/master/aircraft/seminar_series_rc_aircraft_design.m