Originally Posted by Bruce Abbott
Could you fit a curve of thrust vs. rpm to the averages of all those points, then show the derived constants? The curve's equation would be of the form 'thrust = a*rpm^b' (where constant a = thrust.rpm.factor, and b = thrust.rpm.exponent).
I plotted the data in excel and added a trend line and it came up with
thrust = 0.000005*rpm^2.0835
Once I can wrap my head around how excel spit out that value I think I can add a new calculator thats exactly what wjbite is asking for.