Circulation at Origin given Induced Angle of Attack Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Lift Distribution

Elementary Flows

Flow and Lift Distribution

Flow over Airfoils and Wings

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Elliptical Lift Distribution

General Lift Distribution

✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack [α_i]			+10% -10%
✖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.ⓘ Freestream Velocity [V_∞]			+10% -10%

✖Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.ⓘ Circulation at Origin given Induced Angle of Attack [Γ_o]

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Formula

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Circulation at Origin given Induced Angle of Attack

Formula

`"Γ"_{"o"} = 2*"b"*"α"_{"i"}*"V"_{"∞"}`

Example

`"13.92668m²/s"=2*"2340mm"*"11°"*"15.5m/s"`

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Download Elliptical Lift Distribution Formulas PDF

Circulation at Origin given Induced Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity
Γ_o = 2*b*α_i*V_∞
This formula uses 4 Variables

Variables Used

Circulation at Origin - (Measured in Square Meter per Second) - Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Induced Angle of Attack - (Measured in Radian) - The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.
Freestream Velocity - (Measured in Meter per Second) - 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.

STEP 1: Convert Input(s) to Base Unit

Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)
Induced Angle of Attack: 11 Degree --> 0.19198621771934 Radian (Check conversion here)
Freestream Velocity: 15.5 Meter per Second --> 15.5 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Γ_o = 2*b*α_i*V_∞ --> 2*2.34*0.19198621771934*15.5

Evaluating ... ...

Γ_o = 13.9266802333609

STEP 3: Convert Result to Output's Unit

13.9266802333609 Square Meter per Second --> No Conversion Required

FINAL ANSWER

13.9266802333609 ≈ 13.92668 Square Meter per Second <-- Circulation at Origin

(Calculation completed in 00.004 seconds)

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< 20 Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

Go Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Circulation at Origin in Elliptical Lift Distribution

Go Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)

Coefficient of Lift given Circulation at Origin

Go Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin)

Freestream Velocity given Circulation at Origin

Go Freestream Velocity = pi*Wingspan*Circulation at Origin/(2*Reference Area Origin*Lift Coefficient ELD)

Lift of Wing given Circulation at Origin

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

Circulation at Origin given Lift of Wing

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

Induced Angle of Attack given Coefficient of Lift

Go Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)

Circulation at given Distance along Wingspan

Go Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Coefficient of Lift given Induced Drag Coefficient

Go Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)

Aspect Ratio given Induced Drag Coefficient

Go Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)

Induced Drag Coefficient given Aspect Ratio

Go Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)

Induced Angle of Attack given Circulation at Origin

Go Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)

Freestream Velocity given Induced Angle of Attack

Go Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)

Circulation at Origin given Induced Angle of Attack

Go Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity

Induced Angle of Attack given Aspect Ratio

Go Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)

Aspect Ratio given Induced Angle of Attack

Go Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack)

Coefficient of Lift given Induced Angle of Attack

Go Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD

Induced Angle of Attack given Downwash

Go Induced Angle of Attack = -(Downwash/Freestream Velocity)

Downwash in Elliptical Lift Distribution

Go Downwash = -Circulation at Origin/(2*Wingspan)

Circulation at Origin given Downwash

Go Circulation at Origin = -2*Downwash*Wingspan

Circulation at Origin given Induced Angle of Attack Formula

Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity
Γ_o = 2*b*α_i*V_∞

Does circulation causes lift?

The circulation around the wing speeds up the air above it and produces suction slows down the air below, and produces pressure under the wing. Accordingly lift is produced by circulation just as in the case of the lifting cylinder.

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

Circulation at Origin given Induced Angle of Attack calculator uses Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity to calculate 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 calculate Circulation at Origin given Induced Angle of Attack using this online calculator? To use this online calculator 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. Here is how the Circulation at Origin given Induced Angle of Attack calculation can be explained with given input values -> 13.92668 = 2*2.34*0.19198621771934*15.5.

FAQ

What is Circulation at Origin given Induced Angle of Attack?

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 and is represented as Γ_o = 2*b*α_i*V_∞ or Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity. The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, The Induced Angle of Attack is the angle between the local relative wind and the direction of 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.

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

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 is calculated using Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity. To calculate Circulation at Origin given Induced Angle of Attack, you need Wingspan (b), Induced Angle of Attack (α_i) & Freestream Velocity (V_∞). With our tool, you need to enter the respective value for Wingspan, Induced Angle of Attack & Freestream Velocity and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Circulation at Origin?

In this formula, Circulation at Origin uses Wingspan, Induced Angle of Attack & Freestream Velocity. We can use 3 other way(s) to calculate the same, which is/are as follows -

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)

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