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

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient 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 for given required thrust
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift 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 at minimum required thrust Formula

Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
C<sub>D,0</sub>=(C<sub>L</sub>^2)/(pi*e*AR)
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
Zero-lift drag coefficient for given required thrust GO
Lift-induced drag coefficient for given required thrust GO
Zero-lift drag coefficient for given lift coefficient GO

What does the Drag Coefficient indicate?

The drag coefficient indicates not only the complex dependencies of object shape and inclination but also the effects of air viscosity and compressibility.

How to Calculate Zero-lift drag coefficient at minimum required thrust?

Zero-lift drag coefficient at minimum required thrust calculator uses Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) to calculate the Zero-lift drag coefficient, The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag). Zero-lift drag coefficient and is denoted by CD,0 symbol.

How to calculate Zero-lift drag coefficient at minimum required thrust using this online calculator? To use this online calculator for Zero-lift drag coefficient at minimum required thrust, enter lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Zero-lift drag coefficient at minimum required thrust calculation can be explained with given input values -> 15.91549 = (10^2)/(pi*0.5*4).

FAQ

What is Zero-lift drag coefficient at minimum required thrust?
The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag) and is represented as CD,0=(CL^2)/(pi*e*AR) or Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing). The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
How to calculate Zero-lift drag coefficient at minimum required thrust?
The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag) is calculated using Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing). To calculate Zero-lift drag coefficient at minimum required thrust, you need lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing 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 lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing. 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*Reference Area))-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=Coefficient of drag due to lift/3
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