Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Non-dimensional pressure coefficient
Pressure coefficient=Change in static pressure/Dynamic Pressure GO
Moment coefficient
moment coefficient=moment/(Dynamic Pressure*Area*Chord Length) GO
Normal Force Coefficient
coefficient of force=Normal Force/(Dynamic Pressure*Area) GO
Velocity of Fluid When Dynamic Pressure is Given
Fluid Velocity=sqrt(Dynamic Pressure*2/Liquid Density) GO
Density of the Liquid When Dynamic Pressure is Given
Liquid Density=2*Dynamic Pressure/(Fluid Velocity^2) GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO
Axial force coefficient
coefficient of force=Force/(Dynamic Pressure*Area) GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

4 Other formulas that calculate the same Output

Zero-lift drag coefficient for given lift coefficient
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Zero-lift drag coefficient at minimum required thrust
Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Zero-lift drag coefficient for minimum power required
Zero-lift drag coefficient=Coefficient of drag due to lift/3 GO

Zero-lift drag coefficient for given required thrust Formula

Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift
C<sub>D,0</sub>=(T/(P<sub>dynamic*S))-C<sub>D,i</sub>
More formulas
Drag for a level, unaccelerated flight at negligible thrust angle GO
Coefficient of Drag for given thrust-to-weight ratio GO
Coefficient of Drag for given thrust and weight GO
Lift-induced drag coefficient for given required thrust GO
Zero-lift drag coefficient for given lift coefficient GO
Zero-lift drag coefficient at minimum required thrust GO

What is a zero-lift drag?

The drag acting on a body for zero lift force when it is immersed in a fluid is called the zero-lift drag.

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.

FAQ

What is Zero-lift drag coefficient for given required thrust?
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 and is represented as CD,0=(T/(Pdynamic*S))-CD,i or Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift. The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area and The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.
How to calculate Zero-lift drag coefficient for given required thrust?
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 is calculated using Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift. To calculate Zero-lift drag coefficient for given required thrust, you need Thrust of an aircraft (T), Dynamic Pressure (Pdynamic), Reference Area (S) and Coefficient of drag due to lift (CD,i). With our tool, you need to enter the respective value for Thrust of an aircraft, Dynamic Pressure, Reference Area and Coefficient of drag due to lift and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Zero-lift drag coefficient?
In this formula, Zero-lift drag coefficient uses Thrust of an aircraft, Dynamic Pressure, Reference Area and Coefficient of drag due to lift. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift
  • Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
  • Zero-lift drag coefficient=Coefficient of drag due to lift/3
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