FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Lift Coefficient for Cambered Airfoil Formula

Fx Copy

LaTeX Copy

Lift Coefficient for Cambered Airfoil is a dimensionless coefficient that relates the lift generated per unit span to the fluid density around the body, the fluid velocity & reference area. Check FAQs

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

C_L,cam - Lift Coefficient for Cambered Airfoil?α - Angle of Attack?α₀ - Angle of Zero Lift?π - Archimedes' constant?

Lift Coefficient for Cambered Airfoil Example

With values

With units

Only example

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

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

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

1.419 = 2 \cdot 3.1416 \cdot ((10.94) - (-2))

1.419 = 2 \cdot 3.1416 \cdot ((10.94°) - (-2°))

1.419 = 2 \cdot 3.1416 \cdot ((10.94) - (-2))

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aerodynamics » fx Lift Coefficient for Cambered Airfoil

Lift Coefficient for Cambered Airfoil Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C L,cam = 2 \cdot π \cdot ((10.94°) - (-2°))

Next Step Substitute values of Constants

∴

C L,cam = 2 \cdot 3.1416 \cdot ((10.94°) - (-2°))

Next Step Convert Units

∴

C L,cam = 2 \cdot 3.1416 \cdot ((0.1909rad) - (-0.0349rad))

Next Step Prepare to Evaluate

∴

C L,cam = 2 \cdot 3.1416 \cdot ((0.1909) - (-0.0349))

Next Step Evaluate

∴

C L,cam = 1.41902978833414

LAST Step Rounding Answer

∴

C L,cam = 1.419

Lift Coefficient for Cambered Airfoil Formula Elements

Variables

Constants

Lift Coefficient for Cambered Airfoil

Lift Coefficient for Cambered Airfoil is a dimensionless coefficient that relates the lift generated per unit span to the fluid density around the body, the fluid velocity & reference area.

Symbol: C_L,cam

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient for Cambered Airfoil

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

Angle of Zero Lift

The Angle of Zero Lift is the angle of attack at which an airfoil does not produce any lift.

Symbol: α₀

Measurement: AngleUnit: °

Note: Value should be between -3 to 1.5.

Formulas to find Angle of Zero Lift

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 Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory

C L = 2 \cdot π \cdot α

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

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

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 Cambered Airfoil?

Lift Coefficient for Cambered Airfoil evaluator uses Lift Coefficient for Cambered Airfoil = 2*pi*((Angle of Attack)-(Angle of Zero Lift)) to evaluate the Lift Coefficient for Cambered Airfoil, The Lift Coefficient for Cambered Airfoil is a dimensionless quantity that represents the lift generated by the airfoil normalized by dynamic pressure and the airfoil's reference area. For a cambered airfoil, the lift coefficient depends on various factors including the airfoil's shape, angle of attack, camber, and Reynolds number. Lift Coefficient for Cambered Airfoil is denoted by C_L,cam symbol.

How to evaluate Lift Coefficient for Cambered Airfoil using this online evaluator? To use this online evaluator for Lift Coefficient for Cambered Airfoil, enter Angle of Attack (α) & Angle of Zero Lift (α₀) and hit the calculate button.

FAQs on Lift Coefficient for Cambered Airfoil

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

The formula of Lift Coefficient for Cambered Airfoil is expressed as Lift Coefficient for Cambered Airfoil = 2*pi*((Angle of Attack)-(Angle of Zero Lift)). Here is an example- 1.41903 = 2*pi*((0.190939020168144)-((-0.03490658503988))).

How to calculate Lift Coefficient for Cambered Airfoil?

With Angle of Attack (α) & Angle of Zero Lift (α₀) we can find Lift Coefficient for Cambered Airfoil using the formula - Lift Coefficient for Cambered Airfoil = 2*pi*((Angle of Attack)-(Angle of Zero Lift)). This formula also uses Archimedes' constant .

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit