How to Calculate Mean aerodynamic chord for given tail pitching moment coefficient?
Mean aerodynamic chord for given tail pitching moment coefficient calculator uses Mean aerodynamic chord=Pitching moment due to tail/(0.5*Freestream density*(Velocity^2)*Reference Area*Tail pitching moment coefficient) to calculate the Mean aerodynamic chord, The Mean aerodynamic chord for given tail pitching moment coefficient is a function of the pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the tail's pitching moment coefficient. Mean aerodynamic chord and is denoted by c_{ma} symbol.
How to calculate Mean aerodynamic chord for given tail pitching moment coefficient using this online calculator? To use this online calculator for Mean aerodynamic chord for given tail pitching moment coefficient, enter Pitching moment due to tail (M_{t}), Freestream density (ρ_{∞}), Velocity (v), Reference Area (S) and Tail pitching moment coefficient (C_{mt}) and hit the calculate button. Here is how the Mean aerodynamic chord for given tail pitching moment coefficient calculation can be explained with given input values -> 0.000389 = 3/(0.5*1.225*(60^2)*5*0.7).