Zero-lift drag coefficient for given lift coefficient Calculator

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

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust of an aircraft [T]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluidⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖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 for given lift coefficient [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!

Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

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< 4 Other formulas that calculate the same Output

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

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 lift coefficient Formula

Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
CD,0=(T/(Pdynamic*A))-((CL^2)/(pi*e*AR))

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Zero-lift drag coefficient for given required thrust GO

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Zero-lift drag coefficient at minimum required thrust GO

How is the reference area chosen?

The reference area is arbitrary in principle. It is chosen as the area that is characteristic of the object considered. As an example, in aircraft aerodynamics, typically the planform area of the wing is chosen as the reference area for both lift and drag coefficients of the wing.

How to Calculate Zero-lift drag coefficient for given lift coefficient?

Zero-lift drag coefficient for given lift coefficient calculator uses Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) to calculate the Zero-lift drag coefficient, The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft. Zero-lift drag coefficient and is denoted by C_D,0 symbol.

How to calculate Zero-lift drag coefficient for given lift coefficient using this online calculator? To use this online calculator for Zero-lift drag coefficient for given lift coefficient, enter Thrust of an aircraft (T), Dynamic Pressure (P_dynamic), Area (A), 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 for given lift coefficient calculation can be explained with given input values -> -15.715494 = (100/(10*50))-((10^2)/(pi*0.5*4)).

FAQ

What is Zero-lift drag coefficient for given lift coefficient?

The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft and is represented as C_D,0=(T/(P_{dynamic*A))-((C_L^2)/(pi*e*AR))} or Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). 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 area is the amount of two-dimensional space taken up by an object, 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 for given lift coefficient?

The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft is calculated using Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). To calculate Zero-lift drag coefficient for given lift coefficient, you need Thrust of an aircraft (T), Dynamic Pressure (P_dynamic), Area (A), 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 Thrust of an aircraft, Dynamic Pressure, Area, 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 Thrust of an aircraft, Dynamic Pressure, Area, 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=(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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