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Circulation at Origin given Lift of Wing Formula

GoCirculation at Origin in Elliptical Lift Distribution Formula

GoCirculation at Origin given Induced Angle of Attack Formula

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

Γ o = 4 \cdot \frac{F L}{ρ ∞ \cdot V ∞ \cdot b \cdot π}

Γ_o - Circulation at Origin?F_L - Lift Force?ρ_∞ - Freestream Density?V_∞ - Freestream Velocity?b - Wingspan?π - Archimedes' constant?

Circulation at Origin given Lift of Wing Example

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

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

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

14.0074 = 4 \cdot \frac{488.8}{1.225 \cdot 15.5 \cdot 2340 \cdot 3.1416}

14.0074m²/s = 4 \cdot \frac{488.8N}{1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot 3.1416}

14.0074 = 4 \cdot \frac{488.8}{1.225 \cdot 15.5 \cdot 2340 \cdot 3.1416}

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Circulation at Origin given Lift of Wing Solution

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

FIRST Step Consider the formula

Γ o = 4 \cdot \frac{F L}{ρ ∞ \cdot V ∞ \cdot b \cdot π}

Next Step Substitute values of Variables

∴

Γ o = 4 \cdot \frac{488.8N}{1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot π}

Next Step Substitute values of Constants

∴

Γ o = 4 \cdot \frac{488.8N}{1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot 3.1416}

Next Step Convert Units

∴

Γ o = 4 \cdot \frac{488.8N}{1.225kg/m³ \cdot 15.5m/s \cdot 2.34m \cdot 3.1416}

Next Step Prepare to Evaluate

∴

Γ o = 4 \cdot \frac{488.8}{1.225 \cdot 15.5 \cdot 2.34 \cdot 3.1416}

Next Step Evaluate

∴

Γ o = 14.0074045445226m²/s

LAST Step Rounding Answer

∴

Γ o = 14.0074m²/s

Circulation at Origin given Lift of Wing Formula Elements

Variables

Constants

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

Lift Force

The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.

Symbol: F_L

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Lift Force

Freestream Density

Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.

Symbol: ρ_∞

Measurement: DensityUnit: kg/m³

Note: Value can be positive or negative.

Formulas to find Freestream Density

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

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

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 Circulation at Origin

Go Circulation at Origin in Elliptical Lift Distribution

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

Go Circulation at Origin given Induced Angle of Attack

Γ o = 2 \cdot b \cdot α i \cdot V ∞

Go Circulation at Origin given Downwash

Γ o = - 2 \cdot w \cdot b

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 Circulation at Origin given Lift of Wing?

Circulation at Origin given Lift of Wing evaluator uses Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi) to evaluate the Circulation at Origin, The Circulation at Origin given Lift of Wing formula calculates the circulation which is constant for the elliptical lift distribution when the lift and the wingspan are given. Circulation at Origin is denoted by Γ_o symbol.

How to evaluate Circulation at Origin given Lift of Wing using this online evaluator? To use this online evaluator for Circulation at Origin given Lift of Wing, enter Lift Force (F_L), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Wingspan (b) and hit the calculate button.

FAQs on Circulation at Origin given Lift of Wing

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

The formula of Circulation at Origin given Lift of Wing is expressed as Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi). Here is an example- 14.0074 = 4*488.8/(1.225*15.5*2.34*pi).

How to calculate Circulation at Origin given Lift of Wing?

With Lift Force (F_L), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Wingspan (b) we can find Circulation at Origin given Lift of Wing using the formula - Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi). This formula also uses Archimedes' constant .

What are the other ways to Calculate Circulation at Origin?

Here are the different ways to Calculate Circulation at Origin-

Circulation at Origin=2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)
Circulation at Origin=2*Wingspan*Induced Angle of Attack*Freestream Velocity
Circulation at Origin=-2*Downwash*Wingspan

Can the Circulation at Origin given Lift of Wing be negative?

Yes, the Circulation at Origin given Lift of Wing, measured in Momentum Diffusivity can be negative.

Which unit is used to measure Circulation at Origin given Lift of Wing?

Circulation at Origin given Lift of Wing is usually measured using the Square Meter per Second[m²/s] for Momentum Diffusivity. Square Meter per Hour[m²/s], Square Centimeter per Second[m²/s] are the few other units in which Circulation at Origin given Lift of Wing can be measured.

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Circulation at Origin given Lift of Wing Formula

​GoCirculation at Origin in Elliptical Lift Distribution Formula

​GoCirculation at Origin given Induced Angle of Attack Formula

Circulation at Origin given Lift of Wing Example

Circulation at Origin given Lift of Wing Solution

Circulation at Origin given Lift of Wing Formula Elements

Other Formulas to find Circulation at Origin

Other formulas in Elliptical Lift Distribution category

How to Evaluate Circulation at Origin given Lift of Wing?

FAQs on Circulation at Origin given Lift of Wing

Variable Name

GoCirculation at Origin in Elliptical Lift Distribution Formula

GoCirculation at Origin given Induced Angle of Attack Formula