How to Calculate Lift coefficient for given minimum required thrust?
Lift coefficient for given minimum required thrust calculator uses lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) to calculate the lift coefficient, The Lift coefficient for given minimum required thrust for a steady, level flight is a function of the zero-lift drag coefficient of the aircraft. lift coefficient and is denoted by C_{L} symbol.
How to calculate Lift coefficient for given minimum required thrust using this online calculator? To use this online calculator for Lift coefficient for given minimum required thrust, enter Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Thrust of an aircraft (T), Dynamic Pressure (P_{dynamic)}, Reference Area (S) and Zero-lift drag coefficient (C_{D,0}) and hit the calculate button. Here is how the Lift coefficient for given minimum required thrust calculation can be explained with given input values -> 3.530611 = sqrt(pi*0.5*4*((100/(10*5))-0.0161)).