How to Calculate Tail lift coefficient for given pitching moment coefficient?
Tail lift coefficient for given pitching moment coefficient calculator uses Tail Lift Coefficient=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm) to calculate the Tail Lift Coefficient, The Tail lift coefficient for given pitching moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail moment arm. Tail Lift Coefficient and is denoted by C_{Lt} symbol.
How to calculate Tail lift coefficient for given pitching moment coefficient using this online calculator? To use this online calculator for Tail lift coefficient for given pitching moment coefficient, enter Tail pitching moment coefficient (C_{mt}), Reference Area (S), Mean aerodynamic chord (c_{ma}), Tail Efficiency (η), Horizontal tail area (S_{t}) and Horizontal tail moment arm (𝒍_{t}) and hit the calculate button. Here is how the Tail lift coefficient for given pitching moment coefficient calculation can be explained with given input values -> -1.176075 = -0.7*5*0.2/(0.93*0.8*0.8).