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Sorry for being away for so long.
You guys have said that pitch is variable along the whole side of the prop and that the thrust should be calculated for the segments of the prop.
To get ideal results, you would have to divide the prop into an infinite amount of pieces.
Or better yet, find the limit as the amount of pieces goes to infinity. That is, find a function that gives you the thrust for a specific prop with the variable being the number of pieces, and look what the thrust would be as the number of pieces goes to infinity
Sorry for the repetitiveness
TO give you a little background on what I'm going to say
The equation for thrust is
thrust=ct*q*n^2*d^3
ct=coeff. of thrust
q is mass density of air
n= revolutions per second
d=diameter in feet
Output is in pounds
The whole trick in this whole thing is to find the Ct. What I use in the calculator is a regression with the input being angle at 75% of the diameter and the output being the ct. the data was from a trial by NASA, and can be found here. http://naca.larc.nasa.gov/reports/1932/naca-report-378/
I’m wondering if anyone had better methods. I was trying to get some better regressions by collecting data on props and then making a regression for each brand. Anyone have any better answers?
I could make an unloading program, but I’ll have to know how the relative AOA changes compared to speed and rpm. But there is one thing I don’t understand. If the relative AOA is smaller, there is more rpm. But the relative angle is calculated by speed, pitch and rpm. Isn’t this the chicken and the egg thing again
Okay, that’s my very long 2 cents for now.