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Coefficient of Drag due to lift Formula

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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. Check FAQs

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

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

Coefficient of Drag due to lift Example

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Here is how the Coefficient of Drag due to lift equation looks like with Values.

Here is how the Coefficient of Drag due to lift equation looks like with Units.

Here is how the Coefficient of Drag due to lift equation looks like.

0.1926 = \frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4}

0.1926 = \frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4}

0.1926 = \frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4}

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Coefficient of Drag due to lift Solution

Follow our step by step solution on how to calculate Coefficient of Drag due to lift?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C D,i = \frac{{1.1}^{2}}{π \cdot 0.5 \cdot 4}

Next Step Substitute values of Constants

∴

C D,i = \frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4}

Next Step Prepare to Evaluate

∴

C D,i = \frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4}

Next Step Evaluate

∴

C D,i = 0.192577481141193

LAST Step Rounding Answer

∴

C D,i = 0.1926

Coefficient of Drag due to lift Formula Elements

Variables

Constants

Coefficient of Drag due to Lift

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.

Symbol: C_D,i

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Coefficient of Drag due to Lift

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 in Lift and Drag Polar category

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 for given zero-lift drag coefficient

C D = C D,0 + (\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}

How to Evaluate Coefficient of Drag due to lift?

Coefficient of Drag due to lift evaluator uses Coefficient of Drag due to Lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing) to evaluate the Coefficient of Drag due to Lift, The Coefficient of Drag due to lift is a measure of the air resistance caused by the formation of wing-tip vortices, which generates additional drag on an aircraft or rotorcraft, and is influenced by factors such as lift, wing shape, and air density. Coefficient of Drag due to Lift is denoted by C_D,i symbol.

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

FAQs on Coefficient of Drag due to lift

What is the formula to find Coefficient of Drag due to lift?

The formula of Coefficient of Drag due to lift is expressed as Coefficient of Drag due to Lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing). Here is an example- 0.192577 = (1.1^2)/(pi*0.5*4).

How to calculate Coefficient of Drag due to lift?

With Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a Wing (AR) we can find Coefficient of Drag due to lift using the formula - Coefficient of Drag due to Lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing). This formula also uses Archimedes' constant .

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Coefficient of Drag due to lift Formula

Coefficient of Drag due to lift Example

Coefficient of Drag due to lift Solution

Coefficient of Drag due to lift Formula Elements

Other formulas in Lift and Drag Polar category

How to Evaluate Coefficient of Drag due to lift?

FAQs on Coefficient of Drag due to lift

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