hmm Greg, care to elaborate? I'm a bit lost at the moment.. I'm just trying to find the 2 vectors thrust and drag at time (t), and subtract them to find the resulting vector.
If thrust (17600 N) / mass (3800 kg) = 4.63 m/s^2, and
drag is: (0.5 * 1.225 * 0.02 * v(t)^2)
Am i incorrect to say...
IRstuff, point well taken, i made a bonehead division.. 4.63 is correct.
but nevertheless, the resulting Drag coefficient (assuming a reference area of 1 m^2) is still just way too low, 0.001294 just seems strange when i'm looking at the drag coefficient on an airfoil. I know it's...
OK that's a suspicion i had... but here's my thought process, please explain what i'm assuming wrong..
the airframe weighs 3800 kg, and the thrust of the engine is 17600 N. That means that the engine can accelerate a 3800 kg object at 0.46 m/s^2 ... is that correct? no?
hi all, i'm new here...
I'm a computer nerd who enjoy getting into trouble making hobby programming projects, and this time i'm working on a crude aerodynamics engine. problem is, my physics background is, shall we say, limited. Although i do enjoy the learning experience.
Here's my problem...
