Thank you for this video and associated PDF! This is fantastic information and well summarized. It helped me get a good start on where to begin the design process and what parameters are important. The math definitely makes it easier to optimize the design as someone without any intuitive aero experience!
Hi, do you have any theory behind how strong the wing material needs to be? obviously foam is a popular choice, so clearly relatively low tensile materials are game. Would that mean carbon fibre or other composites is overkill? my design is a 12.5kg/m^2 loading(im in the UK), that drops a payload, so loading will drop below 10 after. my AR is 5:1(2mx0.4m planform). And want average speed to max out at 30m/s. I want to know if foam with a composite leading/trailing edge will be enough or even too much. They'll be having CF tubes inside for assembly purposes as well extra support.
The best thing to do is perform the wing tip test. That is assume you have the weight of the aircraft and perform the standard cantilevered beam problem where the root of the wing is fixed to the fuselage and does not move and the tip of wing has a concentrated load of Weight/2.0 Compute the root bending moment and make sure whatever material you have can support that load. Hope that helps!
Thanks a lot. nice explanation. Can you write these things and post them somewhere since what you wrote on the board is not very clear? Or you could upload the video in a higher resolution. Cheers
Hey man. Sorry for the poor quality. I probably need to redo these videos. In the meantime feel free to check this out here. Comment back if some equations are missing. I will be contributing to this textbook over the next few months. github.com/cmontalvo251/LaTeX/blob/master/Aircraft_Flight_Mechanics/Aircraft_Flight_Mechanics.pdf
With your advanced background I am shocked u believe in wing cube loading myth....No derivation of lift equation gives cube root. Our desired term is Velocity & v=Constant*(W/A)^0.5 or Scale velocity v/l=(Constant/l)*(W/A)^0.5....even if we approximate l=A^.5 that too results in v/l=constant*W^0.5/A^0.25 "no cube roots".......Get over it & I tested cube roots on full size aircraft like C130 & u get totally absurd answers....Rule of math is limit =0.00001 & limit=1000000000 must be satisfied...but cube root collapses
@@CarlosMontalvo251 Promote a term that is scientifically proven & works across the board...People will be designing better aircrafts & world will be a better place... Root of wing loading for stall speed comparison & Root of wing loading/aircraft length for scale speed comparison.
Thanks for the awesome pdf. The aerodynamic calculations / simulations really remove much of the guess work and i build 1 aircraft with this method and the flight performance was great, but i still need to work on the structural engineering to makes something that does not start to oscillate at higher speeds.
Great name you picked. I already knew more than I wanted to about Montecarlo simulations. Now that I found you again I’ll save the link. I’m an RC flyer 83 years old and a licensed glider pilot who hasn’t flown for forty or so year.
Let’s not forget that in competition sailplanes use water ballast to improve their penetration. The L/D remains the same but it and stall etc all occur at higher speeds. The water is dumped in weak lift or before landing so that the weight of the water doesn’t risk damaging the glider in landing.
Very well explained. Only draw back is that I’m straining to see what’s on the white board. Have you any suggestions on other videos on the same topic?
Hey Erlina, sorry about that. I made these during COVID and was having trouble with my camera. I have published an open source textbook that you can easily read here. github.com/cmontalvo251/LaTeX/blob/master/Aerospace_Mechanics/aerospace_mechanics.pdf I believe you will find all the equations you need and if you don't let me know and I can add them
The wing loading values I posted come from multiple sources and are actually the Wing Cube Loading which is in oz/ft^3 Here's a great article explaining it in more detail
