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Coefficient of Lift for Airfoil Formula

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Lift Coefficient for Airfoil is a 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. Check FAQs

C L airfoil = 2 \cdot π \cdot \sin (α)

C_{L airfoil} - Lift Coefficient for Airfoil?α - Angle of Attack on Airfoil?π - Archimedes' constant?

Coefficient of Lift for Airfoil Example

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Here is how the Coefficient of Lift for Airfoil equation looks like with Values.

Here is how the Coefficient of Lift for Airfoil equation looks like with Units.

Here is how the Coefficient of Lift for Airfoil equation looks like.

0.7113 = 2 \cdot 3.1416 \cdot \sin (6.5)

0.7113 = 2 \cdot 3.1416 \cdot \sin (6.5°)

0.7113 = 2 \cdot 3.1416 \cdot \sin (6.5)

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Coefficient of Lift for Airfoil Solution

Follow our step by step solution on how to calculate Coefficient of Lift for Airfoil?

FIRST Step Consider the formula

C L airfoil = 2 \cdot π \cdot \sin (α)

Next Step Substitute values of Variables

∴

C L airfoil = 2 \cdot π \cdot \sin (6.5°)

Next Step Substitute values of Constants

∴

C L airfoil = 2 \cdot 3.1416 \cdot \sin (6.5°)

Next Step Convert Units

∴

C L airfoil = 2 \cdot 3.1416 \cdot \sin (0.1134rad)

Next Step Prepare to Evaluate

∴

C L airfoil = 2 \cdot 3.1416 \cdot \sin (0.1134)

Next Step Evaluate

∴

C L airfoil = 0.711276769471888

LAST Step Rounding Answer

∴

C L airfoil = 0.7113

Coefficient of Lift for Airfoil Formula Elements

Variables

Constants

Functions

Lift Coefficient for Airfoil

Lift Coefficient for Airfoil is a 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 airfoil}

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient for Airfoil

Angle of Attack on Airfoil

Angle of Attack on Airfoil is the angle between a reference line on an airfoil and the vector representing the relative motion between the airfoil and the fluid through which it is moving.

Symbol: α

Measurement: AngleUnit: °

Note: Value should be greater than 0.

Formulas to find Angle of Attack on Airfoil

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

sin

Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse.

Syntax: sin(Angle)

Other formulas in Lift and Circulation category

Go Circulation developed on Airfoil

Γ = π \cdot U \cdot C \cdot \sin (α)

Go Chord Length for Circulation developed on Airfoil

C = \frac{Γ}{π \cdot U \cdot \sin (α)}

Go Angle of Attack for Circulation developed on Airfoil

α = a \sin (\frac{Γ}{π \cdot U \cdot C})

Go Angle of Attack for Lift Coefficient on Airfoil

α = a \sin (\frac{C L airfoil}{2 \cdot π})

How to Evaluate Coefficient of Lift for Airfoil?

Coefficient of Lift for Airfoil evaluator uses Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil) to evaluate the Lift Coefficient for Airfoil, The Coefficient of lift for airfoil formula is defined as a 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 and is calculated while considering the value of two pi and sin with an angle. This angle is considered as the angle of attack. Lift Coefficient for Airfoil is denoted by C_{L airfoil} symbol.

How to evaluate Coefficient of Lift for Airfoil using this online evaluator? To use this online evaluator for Coefficient of Lift for Airfoil, enter Angle of Attack on Airfoil (α) and hit the calculate button.

FAQs on Coefficient of Lift for Airfoil

What is the formula to find Coefficient of Lift for Airfoil?

The formula of Coefficient of Lift for Airfoil is expressed as Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil). Here is an example- 0.711277 = 2*pi*sin(0.11344640137961).

How to calculate Coefficient of Lift for Airfoil?

With Angle of Attack on Airfoil (α) we can find Coefficient of Lift for Airfoil using the formula - Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil). This formula also uses Archimedes' constant and Sine function(s).

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