How to Calculate Coefficient of Pitching Moment Respect to Fuselage Contribution?
Coefficient of Pitching Moment Respect to Fuselage Contribution calculator uses Moment Coefficient For Fuselage Contribution = (1/(36.5*Wing Area*Wingspan))*sum(x,0,Wingspan/2,Average Width Of Fuselage^2*(Wing Zero Lift Angle+Incidence Of Fuselage Camber Line)*Length Of Fuselage Increment) to calculate the Moment Coefficient For Fuselage Contribution, The Coefficient of pitching moment respect to fuselage contribution, often denoted as fuselage measures the change in pitching moment per unit change in a parameter related to the fuselage. This parameter could be the angle of attack, sideslip angle, or another relevant factor. Moment Coefficient For Fuselage Contribution is denoted by Cm_{0,f} symbol.
How to calculate Coefficient of Pitching Moment Respect to Fuselage Contribution using this online calculator? To use this online calculator for Coefficient of Pitching Moment Respect to Fuselage Contribution, enter Wing Area (S), Wingspan (b), Average Width Of Fuselage (w_{f}), Wing Zero Lift Angle (α_{0,w}), Incidence Of Fuselage Camber Line (i_{f}) & Length Of Fuselage Increment (Δx) and hit the calculate button. Here is how the Coefficient of Pitching Moment Respect to Fuselage Contribution calculation can be explained with given input values -> 0.001507 = (1/(36.5*184*20))*sum(x,0,20/2,2^2*(0.3+2)*2).