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/(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 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 (T), Dynamic Pressure (Pdynamic), Reference Area (S) & 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 -> 0.686 = (100/(10*8))-0.93.