It would be really helpful if u could touch more upon the results of the various graphs that are relevant to aircraft conceptual design... Like the one u said about elliptical curve and positive slope for Cl v Cd...

Very usefull thanks!

Hi . When I run VSPAERO launch solver . Results are not shown and graph appears to be blank. Some options are grey . What should I do

Hi again, I have a question: In VSP Aero, Mach number was set as 0. But after the graphs are plotted, we see that a Mach number is evaluated based on the altitude and flow velocity given. Why inserting M=0 in variables do not create a problem? (We only varied alpha and inserted 0 as M, but M did not stay as zero.)

Hi, this was really helpful, thank you very much. I will make an opimization between wing volume and fuselage volume in order to reach some desired objectives. I'm considering to use OpenVSP for geometrical changes. What is the easiest way to change gepmetrical parameters automatically in OpenVSP? For example, let's say that the chord length and span will change such that Cl/Cd would be the greatest? Where can I reach you, if you are willing to help? Thank you so much in advance!

I tried to take parasite drag of a wing alone and I couldn't able to obtain the values could you please help me

Thanks for the tutorial, with that data, how to calculate the engine hp?

If you need to visualize basic aerodynamics exporting STL on the fastest algorithm: Fluidx3D kzfaq.info/get/bejne/fcqPgKh5tcvHp2Q.html

Yang sayang aku like yang cinta allah coment.