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 CD,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 (Pdynamic), Reference Area (S) and Coefficient of drag due to lift (CD,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.