Circulation at Origin given Induced Angle of Attack Calculator

✖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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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 00.020 seconds)

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< Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

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

Circulation at given Distance along Wingspan

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

Induced Angle of Attack given Aspect Ratio

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

Downwash in Elliptical Lift Distribution

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

Circulation at Origin given Induced Angle of Attack Formula

LaTeX Go

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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