drgondog
Major
Zipper, There is a reason that books on Aero or Performance wave their arms in the air and state "assume prop efficiency is 0.80 (0.85)", and glib step into Thrust HP discussions. Most high performance props fit into that bandwidth. Ditto for Oswald efficiency. I'm too old and tired to devote a lot of cycles on helping you learn differential and integral calculus and the aerodynamics of propeller blades. BTW props have both Lift and Drag as a function of angle, blade section, chord, and radius from axis. Essentially if you wish to develop a Center of Pressure, integrated CL and CD, and spanwise pressure distribution - you must integrate the spanwise airfoil sections as a function of relative angle of attack, wing twist and chord. For 3-D wing, assuming a spanwise rotation from a lifting line to account for induced drag componentWhile this is a crash-course for me: Having found some data on general aviation propellers, which may not work because of the fact that the older props generally had variations in chord and C/L as a function of radius from center to tip, and the formulas described don't factor in variable chord and CL as a function of radius as well as some searching on Google.
no.It appears that ß = blade angel; b = blade section in feet (I assume this is the chord); while I'm not sure what the difference between integrated and coefficient of lift, IIRC: Coefficient of lift was basically the amount of lift provided to calculated dynamic pressure or force (BTW: Does coefficient of lift and coefficient of thrust on a propeller mean the same thing?)