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Circulation at Origin given Induced Angle of Attack Formula

GoCirculation at Origin in Elliptical Lift Distribution Formula

GoCirculation at Origin given Downwash 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 = 2 \cdot b \cdot α i \cdot V ∞

Γ_o - Circulation at Origin?b - Wingspan?α_i - Induced Angle of Attack?V_∞ - Freestream Velocity?

Circulation at Origin given Induced Angle of Attack Example

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Here is how the Circulation at Origin given Induced Angle of Attack equation looks like with Values.

Here is how the Circulation at Origin given Induced Angle of Attack equation looks like with Units.

Here is how the Circulation at Origin given Induced Angle of Attack equation looks like.

13.9267 = 2 \cdot 2340 \cdot 11 \cdot 15.5

13.9267m²/s = 2 \cdot 2340mm \cdot 11° \cdot 15.5m/s

13.9267 = 2 \cdot 2340 \cdot 11 \cdot 15.5

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Circulation at Origin given Induced Angle of Attack Solution

Follow our step by step solution on how to calculate Circulation at Origin given Induced Angle of Attack?

FIRST Step Consider the formula

Γ o = 2 \cdot b \cdot α i \cdot V ∞

Next Step Substitute values of Variables

∴

Γ o = 2 \cdot 2340mm \cdot 11° \cdot 15.5m/s

Next Step Convert Units

∴

Γ o = 2 \cdot 2.34m \cdot 0.192rad \cdot 15.5m/s

Next Step Prepare to Evaluate

∴

Γ o = 2 \cdot 2.34 \cdot 0.192 \cdot 15.5

Next Step Evaluate

∴

Γ o = 13.9266802333609m²/s

LAST Step Rounding Answer

∴

Γ o = 13.9267m²/s

Circulation at Origin given Induced Angle of Attack Formula Elements

Variables

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

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

Induced Angle of Attack

The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

Symbol: α_i

Measurement: AngleUnit: °

Note: Value can be positive or negative.

Formulas to find Induced Angle of Attack

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

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 Downwash

Γ o = - 2 \cdot w \cdot b

Go Circulation at Origin given Lift of Wing

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

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 Induced Angle of Attack?

Circulation at Origin given Induced Angle of Attack evaluator uses Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity to evaluate the Circulation at Origin, The Circulation at Origin given Induced Angle of Attack formula calculates the circulation which is constant for the elliptical lift distribution when the induced angle of attack and the wingspan is given. Circulation at Origin is denoted by Γ_o symbol.

How to evaluate Circulation at Origin given Induced Angle of Attack using this online evaluator? To use this online evaluator for Circulation at Origin given Induced Angle of Attack, enter Wingspan (b), Induced Angle of Attack (α_i) & Freestream Velocity (V_∞) and hit the calculate button.

FAQs on Circulation at Origin given Induced Angle of Attack

What is the formula to find Circulation at Origin given Induced Angle of Attack?

The formula of Circulation at Origin given Induced Angle of Attack is expressed as Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity. Here is an example- 13.92668 = 2*2.34*0.19198621771934*15.5.

How to calculate Circulation at Origin given Induced Angle of Attack?

With Wingspan (b), Induced Angle of Attack (α_i) & Freestream Velocity (V_∞) we can find Circulation at Origin given Induced Angle of Attack using the formula - Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity.

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*Downwash*Wingspan
Circulation at Origin=4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)

Can the Circulation at Origin given Induced Angle of Attack be negative?

Yes, the Circulation at Origin given Induced Angle of Attack, measured in Momentum Diffusivity can be negative.

Which unit is used to measure Circulation at Origin given Induced Angle of Attack?

Circulation at Origin given Induced Angle of Attack 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 Induced Angle of Attack can be measured.

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Circulation at Origin given Induced Angle of Attack Formula

​GoCirculation at Origin in Elliptical Lift Distribution Formula

​GoCirculation at Origin given Downwash Formula

Circulation at Origin given Induced Angle of Attack Example

Circulation at Origin given Induced Angle of Attack Solution

Circulation at Origin given Induced Angle of Attack Formula Elements

Other Formulas to find Circulation at Origin

Other formulas in Elliptical Lift Distribution category

How to Evaluate Circulation at Origin given Induced Angle of Attack?

FAQs on Circulation at Origin given Induced Angle of Attack

Variable Name

GoCirculation at Origin in Elliptical Lift Distribution Formula

GoCirculation at Origin given Downwash Formula