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Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory Formula

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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. Check FAQs

C L = 2 \cdot π \cdot α

C_L - Lift Coefficient?α - Angle of Attack?π - Archimedes' constant?

Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory Example

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Here is how the Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory equation looks like with Values.

Here is how the Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory equation looks like with Units.

Here is how the Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory equation looks like.

1.1997 = 2 \cdot 3.1416 \cdot 10.94

1.1997 = 2 \cdot 3.1416 \cdot 10.94°

1.1997 = 2 \cdot 3.1416 \cdot 10.94

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Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory Solution

Follow our step by step solution on how to calculate Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory?

FIRST Step Consider the formula

C L = 2 \cdot π \cdot α

Next Step Substitute values of Variables

∴

C L = 2 \cdot π \cdot 10.94°

Next Step Substitute values of Constants

∴

C L = 2 \cdot 3.1416 \cdot 10.94°

Next Step Convert Units

∴

C L = 2 \cdot 3.1416 \cdot 0.1909rad

Next Step Prepare to Evaluate

∴

C L = 2 \cdot 3.1416 \cdot 0.1909

Next Step Evaluate

∴

C L = 1.19970524608775

LAST Step Rounding Answer

∴

C L = 1.1997

Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory Formula Elements

Variables

Constants

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

Angle of Attack

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

Symbol: α

Measurement: AngleUnit: °

Note: Value can be positive or negative.

Formulas to find Angle of Attack

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 Flow over Airfoils category

Go Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory

C m,le = - \frac{C L}{4}

Go Lift Coefficient for Cambered Airfoil

C L,cam = 2 \cdot π \cdot ((α) - (α 0))

Go Center of Pressure Location for Cambered Airfoil

x cp = - \frac{C m,le \cdot c}{C L}

Go Boundary Layer Thickness for Laminar Flow

δ L = 5 \cdot \frac{x}{\sqrt{Re L}}

How to Evaluate Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory?

Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory evaluator uses Lift Coefficient = 2*pi*Angle of Attack to evaluate the Lift Coefficient, The Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory formula, the lift coefficient for a symmetrical airfoil is determined by the angle of attack, The lift coefficient increases linearly with the angle of attack according to the formula. Lift Coefficient is denoted by C_L symbol.

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

FAQs on Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory

What is the formula to find Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory?

The formula of Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory is expressed as Lift Coefficient = 2*pi*Angle of Attack. Here is an example- 1.199705 = 2*pi*0.190939020168144.

How to calculate Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory?

With Angle of Attack (α) we can find Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory using the formula - Lift Coefficient = 2*pi*Angle of Attack. This formula also uses Archimedes' constant .

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