Sorry for the reshare had some issues at first with AoA. Just mess around with the sliders. Disclaimers: -All values are in metric(m(metres), kg(kilograms), s(seconds), N(Newtons), °(degrees), °C(Celsius)) NOT aeronautical. NOT SI. -The airfoil data is approximated from a NACA 0015 airfoil. -All calculations with a mach number greater than 1 are unreliable(might update it later lol) -The air density approximation is so scuffed lol. -Default data is approximated from an F-16 lol. -Everything is an approximation. Pls don't use this for serious applications (duh).
Take the span efficiencies from here (use the final column): https://www.fzt.haw-hamburg.de/pers/Scholz//OPerA/OPerA_PUB_DLRK_12-09-10_Appendix_A_with_e_calc.pdf Take the 0 lift drag coefficients from here: https://aviation.stackexchange.com/questions/43410/how-is-the-zero-lift-drag-coefficient-calculated Credits: Past 120 years of aviation research ig lol. Wikipedia Aviation stack exchange Me after finishing this project: https://scratch.mit.edu/discuss/youtube/YRL4uIVzVWI/
