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Drag Coefficient for given zero-lift drag coefficient Formula

GoDrag Coefficient for given parasite drag coefficient Formula

GoDrag coefficient given Drag Force Formula

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Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water. Check FAQs

C D = C D,0 + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

C_D - Drag Coefficient?C_D,0 - Zero-Lift Drag Coefficient?C_L - Lift Coefficient?e_oswald - Oswald Efficiency Factor?AR - Aspect Ratio of a Wing?π - Archimedes' constant?

Drag Coefficient for given zero-lift drag coefficient Example

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Here is how the Drag Coefficient for given zero-lift drag coefficient equation looks like with Values.

Here is how the Drag Coefficient for given zero-lift drag coefficient equation looks like with Units.

Here is how the Drag Coefficient for given zero-lift drag coefficient equation looks like.

30.0926 = 29.9 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

30.0926 = 29.9 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

30.0926 = 29.9 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

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Drag Coefficient for given zero-lift drag coefficient Solution

Follow our step by step solution on how to calculate Drag Coefficient for given zero-lift drag coefficient?

FIRST Step Consider the formula

C D = C D,0 + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Next Step Substitute values of Variables

∴

C D = 29.9 + (\frac{{1.1}^{2}}{π \cdot 0.5 \cdot 4})

Next Step Substitute values of Constants

∴

C D = 29.9 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

Next Step Prepare to Evaluate

∴

C D = 29.9 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

Next Step Evaluate

∴

C D = 30.0925774811412

LAST Step Rounding Answer

∴

C D = 30.0926

Drag Coefficient for given zero-lift drag coefficient Formula Elements

Variables

Constants

Drag Coefficient

Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

Symbol: C_D

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Drag Coefficient

Zero-Lift Drag Coefficient

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.

Symbol: C_D,0

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Zero-Lift Drag Coefficient

Lift Coefficient

The Lift Coefficient 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.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Oswald Efficiency Factor

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.

Symbol: e_oswald

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Oswald Efficiency Factor

Aspect Ratio of a Wing

The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Aspect Ratio of a Wing

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

Other Formulas to find Drag Coefficient

Go Drag Coefficient for given parasite drag coefficient

C D = C D,e + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Drag coefficient given Drag Force

C D = \frac{F D}{q}

Go Coefficient of drag given drag

C D = \frac{C L \cdot F D}{W 0}

Go Drag coefficient given lift coefficient

C D = C L \cdot \frac{F D}{F L}

Other formulas in Lift and Drag Polar category

Go Coefficient of Drag due to lift

C D,i = \frac{{C L}^{2}}{π \cdot e oswald \cdot AR}

Go Parasite Drag Coefficient at zero lift

C D,0 = C D - C D,i

Go Modern Lift Equation

L = \frac{C L \cdot ρ air \cdot S \cdot {u f}^{2}}{2}

Go Lift coefficient given Lift Force

C L = \frac{F L}{q}

How to Evaluate Drag Coefficient for given zero-lift drag coefficient?

Drag Coefficient for given zero-lift drag coefficient evaluator uses Drag Coefficient = Zero-Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)) to evaluate the Drag Coefficient, Drag Coefficient for given zero-lift drag coefficient is a measure of the overall aerodynamic drag of an object, calculated by combining the zero-lift drag coefficient, lift coefficient, Oswald efficiency factor, and aspect ratio of the wing. Drag Coefficient is denoted by C_D symbol.

How to evaluate Drag Coefficient for given zero-lift drag coefficient using this online evaluator? To use this online evaluator for Drag Coefficient for given zero-lift drag coefficient, enter Zero-Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a Wing (AR) and hit the calculate button.

FAQs on Drag Coefficient for given zero-lift drag coefficient

What is the formula to find Drag Coefficient for given zero-lift drag coefficient?

The formula of Drag Coefficient for given zero-lift drag coefficient is expressed as Drag Coefficient = Zero-Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). Here is an example- 29.39258 = 29.9+((1.1^2)/(pi*0.5*4)).

How to calculate Drag Coefficient for given zero-lift drag coefficient?

With Zero-Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a Wing (AR) we can find Drag Coefficient for given zero-lift drag coefficient using the formula - Drag Coefficient = Zero-Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). This formula also uses Archimedes' constant .

What are the other ways to Calculate Drag Coefficient?

Here are the different ways to Calculate Drag Coefficient-

Drag Coefficient=Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))
Drag Coefficient=Drag Force/Dynamic Pressure
Drag Coefficient=(Lift Coefficient*Drag Force)/Gross Weight

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Drag Coefficient for given zero-lift drag coefficient Formula

​GoDrag Coefficient for given parasite drag coefficient Formula

​GoDrag coefficient given Drag Force Formula

Drag Coefficient for given zero-lift drag coefficient Example

Drag Coefficient for given zero-lift drag coefficient Solution

Drag Coefficient for given zero-lift drag coefficient Formula Elements

Other Formulas to find Drag Coefficient

Other formulas in Lift and Drag Polar category

How to Evaluate Drag Coefficient for given zero-lift drag coefficient?

FAQs on Drag Coefficient for given zero-lift drag coefficient

Variable Name

GoDrag Coefficient for given parasite drag coefficient Formula

GoDrag coefficient given Drag Force Formula