FormulaDen.com

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

Coefficient of Lift given Circulation at Origin Formula

GoCoefficient of Lift given Induced Drag Coefficient Formula

GoCoefficient of Lift given Induced Angle of Attack Formula

Fx Copy

LaTeX Copy

The Lift Coefficient ELD 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,ELD = π \cdot b \cdot \frac{Γ o}{2 \cdot V ∞ \cdot S 0}

C_L,ELD - Lift Coefficient ELD?b - Wingspan?Γ_o - Circulation at Origin?V_∞ - Freestream Velocity?S₀ - Reference Area Origin?π - Archimedes' constant?

Coefficient of Lift given Circulation at Origin Example

With values

With units

Only example

Here is how the Coefficient of Lift given Circulation at Origin equation looks like with Values.

Here is how the Coefficient of Lift given Circulation at Origin equation looks like with Units.

Here is how the Coefficient of Lift given Circulation at Origin equation looks like.

1.5022 = 3.1416 \cdot 2340 \cdot \frac{14}{2 \cdot 15.5 \cdot 2.21}

1.5022 = 3.1416 \cdot 2340mm \cdot \frac{14m²/s}{2 \cdot 15.5m/s \cdot 2.21m²}

1.5022 = 3.1416 \cdot 2340 \cdot \frac{14}{2 \cdot 15.5 \cdot 2.21}

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 Coefficient of Lift given Circulation at Origin

Coefficient of Lift given Circulation at Origin Solution

Follow our step by step solution on how to calculate Coefficient of Lift given Circulation at Origin?

FIRST Step Consider the formula

C L,ELD = π \cdot b \cdot \frac{Γ o}{2 \cdot V ∞ \cdot S 0}

Next Step Substitute values of Variables

∴

C L,ELD = π \cdot 2340mm \cdot \frac{14m²/s}{2 \cdot 15.5m/s \cdot 2.21m²}

Next Step Substitute values of Constants

∴

C L,ELD = 3.1416 \cdot 2340mm \cdot \frac{14m²/s}{2 \cdot 15.5m/s \cdot 2.21m²}

Next Step Convert Units

∴

C L,ELD = 3.1416 \cdot 2.34m \cdot \frac{14m²/s}{2 \cdot 15.5m/s \cdot 2.21m²}

Next Step Prepare to Evaluate

∴

C L,ELD = 3.1416 \cdot 2.34 \cdot \frac{14}{2 \cdot 15.5 \cdot 2.21}

Next Step Evaluate

∴

C L,ELD = 1.50224164839588

LAST Step Rounding Answer

∴

C L,ELD = 1.5022

Coefficient of Lift given Circulation at Origin Formula Elements

Variables

Constants

Lift Coefficient ELD

The Lift Coefficient ELD 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,ELD

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient ELD

Wingspan

The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

Symbol: b

Measurement: LengthUnit: mm

Note: Value should be greater than 0.

Formulas to find Wingspan

Circulation at Origin

Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.

Symbol: Γ_o

Measurement: Momentum DiffusivityUnit: m²/s

Note: Value can be positive or negative.

Formulas to find Circulation at Origin

Freestream Velocity

The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.

Symbol: V_∞

Measurement: SpeedUnit: m/s

Note: Value can be positive or negative.

Formulas to find Freestream Velocity

Reference Area Origin

Reference Area Origin is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area.

Symbol: S₀

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area Origin

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 Lift Coefficient ELD

Go Coefficient of Lift given Induced Drag Coefficient

C L,ELD = \sqrt{π \cdot AR ELD \cdot C D,i,ELD}

Go Coefficient of Lift given Induced Angle of Attack

C L,ELD = π \cdot α i \cdot AR ELD

Other formulas in Elliptical Lift Distribution category

Go Circulation at given Distance along Wingspan

Γ = Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Lift at given Distance along Wingspan

L = ρ ∞ \cdot V ∞ \cdot Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Downwash in Elliptical Lift Distribution

w = - \frac{Γ o}{2 \cdot b}

Go Induced Angle of Attack given Aspect Ratio

α i = \frac{C l}{π \cdot AR ELD}

How to Evaluate Coefficient of Lift given Circulation at Origin?

Coefficient of Lift given Circulation at Origin evaluator uses Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin) to evaluate the Lift Coefficient ELD, The Coefficient of Lift given Circulation at Origin formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing. Lift Coefficient ELD is denoted by C_L,ELD symbol.

How to evaluate Coefficient of Lift given Circulation at Origin using this online evaluator? To use this online evaluator for Coefficient of Lift given Circulation at Origin, enter Wingspan (b), Circulation at Origin (Γ_o), Freestream Velocity (V_∞) & Reference Area Origin (S₀) and hit the calculate button.

FAQs on Coefficient of Lift given Circulation at Origin

What is the formula to find Coefficient of Lift given Circulation at Origin?

The formula of Coefficient of Lift given Circulation at Origin is expressed as Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin). Here is an example- 1.502242 = pi*2.34*14/(2*15.5*2.21).

How to calculate Coefficient of Lift given Circulation at Origin?

With Wingspan (b), Circulation at Origin (Γ_o), Freestream Velocity (V_∞) & Reference Area Origin (S₀) we can find Coefficient of Lift given Circulation at Origin using the formula - Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin). This formula also uses Archimedes' constant .

What are the other ways to Calculate Lift Coefficient ELD?

Here are the different ways to Calculate Lift Coefficient ELD-

Lift Coefficient ELD=sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)
Lift Coefficient ELD=pi*Induced Angle of Attack*Wing Aspect Ratio ELD

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Coefficient of Lift given Circulation at Origin Formula

​GoCoefficient of Lift given Induced Drag Coefficient Formula

​GoCoefficient of Lift given Induced Angle of Attack Formula

Coefficient of Lift given Circulation at Origin Example

Coefficient of Lift given Circulation at Origin Solution

Coefficient of Lift given Circulation at Origin Formula Elements

Other Formulas to find Lift Coefficient ELD

Other formulas in Elliptical Lift Distribution category

How to Evaluate Coefficient of Lift given Circulation at Origin?

FAQs on Coefficient of Lift given Circulation at Origin

Variable Name

GoCoefficient of Lift given Induced Drag Coefficient Formula

GoCoefficient of Lift given Induced Angle of Attack Formula