How to Calculate Zero-lift drag coefficient for given lift coefficient?
Zero-lift drag coefficient for given lift coefficient calculator uses Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) to calculate the Zero-lift drag coefficient, The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft. Zero-lift drag coefficient and is denoted by C_{D,0} symbol.
How to calculate Zero-lift drag coefficient for given lift coefficient using this online calculator? To use this online calculator for Zero-lift drag coefficient for given lift coefficient, enter Thrust of an aircraft (T), Dynamic Pressure (P_{dynamic)}, Area (A), lift coefficient (C_{L}), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Zero-lift drag coefficient for given lift coefficient calculation can be explained with given input values -> -15.715494 = (100/(10*50))-((10^2)/(pi*0.5*4)).