How to Calculate Zero-lift drag coefficient for given required thrust?
Zero-lift drag coefficient for given required thrust calculator uses Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift to calculate the Zero-lift drag coefficient, The Zero-lift drag coefficient for given required thrust in a steady, level flight depends upon the coefficient of drag due to lift of an aircraft. Zero-lift drag coefficient and is denoted by C_{D,0} symbol.
How to calculate Zero-lift drag coefficient for given required thrust using this online calculator? To use this online calculator for Zero-lift drag coefficient for given required thrust, enter Thrust of an aircraft (T), Dynamic Pressure (P_{dynamic)}, Reference Area (S) and Coefficient of drag due to lift (C_{D,i}) and hit the calculate button. Here is how the Zero-lift drag coefficient for given required thrust calculation can be explained with given input values -> 1.2 = (100/(10*5))-0.8.