Zero-lift drag coefficient at minimum required thrust Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Drag during Level Unaccelerated Flight ↺

✖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. ⓘ lift coefficient [C_L]			+10% -10%
✖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ⓘ Oswald efficiency factor [e]			+10% -10%
✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]			+10% -10%

✖The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitudeⓘ Zero-lift drag coefficient at minimum required thrust [C_D,0]

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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 C_D,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 (C_L), 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 C_D,0=(C_L^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 (C_L), 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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