Circulation at Origin in Elliptical Lift Distribution Calculator

✖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%
✖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.ⓘ Reference Area Origin [S₀]			+10% -10%
✖Lift Coefficient Origin 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.ⓘ Lift Coefficient Origin [C_l]			+10% -10%
✖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%

✖Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.ⓘ Circulation at Origin in Elliptical Lift Distribution [Γ_o]

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Circulation at Origin in Elliptical Lift Distribution Solution

STEP 0: Pre-Calculation Summary

Formula Used

Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)
Γ_o = 2*V_∞*S₀*C_l/(pi*b)
This formula uses 1 Constants, 5 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

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.
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.
Reference Area Origin - (Measured in Square Meter) - 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.
Lift Coefficient Origin - Lift Coefficient Origin 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.
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.

STEP 1: Convert Input(s) to Base Unit

Freestream Velocity: 15.5 Meter per Second --> 15.5 Meter per Second No Conversion Required
Reference Area Origin: 2.21 Square Meter --> 2.21 Square Meter No Conversion Required
Lift Coefficient Origin: 1.5 --> No Conversion Required
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Γ_o = 2*V_∞*S₀*C_l/(pi*b) --> 2*15.5*2.21*1.5/(pi*2.34)

Evaluating ... ...

Γ_o = 13.9791091682381

STEP 3: Convert Result to Output's Unit

13.9791091682381 Square Meter per Second --> No Conversion Required

FINAL ANSWER

13.9791091682381 ≈ 13.97911 Square Meter per Second <-- Circulation at Origin

(Calculation completed in 00.004 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 in Elliptical Lift Distribution Formula

LaTeX Go

Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)
Γ_o = 2*V_∞*S₀*C_l/(pi*b)

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 in Elliptical Lift Distribution?

Circulation at Origin in Elliptical Lift Distribution calculator uses Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan) to calculate the Circulation at Origin, The Circulation at Origin in Elliptical Lift Distribution formula calculates the circulation which is constant for the elliptical lift distribution when the coefficient of lift and the wingspan are given. Circulation at Origin is denoted by Γ_o symbol.

How to calculate Circulation at Origin in Elliptical Lift Distribution using this online calculator? To use this online calculator for Circulation at Origin in Elliptical Lift Distribution, enter Freestream Velocity (V_∞), Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b) and hit the calculate button. Here is how the Circulation at Origin in Elliptical Lift Distribution calculation can be explained with given input values -> 13.97911 = 2*15.5*2.21*1.5/(pi*2.34).

FAQ

What is Circulation at Origin in Elliptical Lift Distribution?

The Circulation at Origin in Elliptical Lift Distribution formula calculates the circulation which is constant for the elliptical lift distribution when the coefficient of lift and the wingspan are given and is represented as Γ_o = 2*V_∞*S₀*C_l/(pi*b) or Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan). 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, 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, Lift Coefficient Origin 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 & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

How to calculate Circulation at Origin in Elliptical Lift Distribution?

The Circulation at Origin in Elliptical Lift Distribution formula calculates the circulation which is constant for the elliptical lift distribution when the coefficient of lift and the wingspan are given is calculated using Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan). To calculate Circulation at Origin in Elliptical Lift Distribution, you need Freestream Velocity (V_∞), Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b). With our tool, you need to enter the respective value for Freestream Velocity, Reference Area Origin, Lift Coefficient Origin & Wingspan 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 Freestream Velocity, Reference Area Origin, Lift Coefficient Origin & Wingspan. We can use 3 other way(s) to calculate the same, which is/are as follows -

Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity
Circulation at Origin = -2*Downwash*Wingspan
Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)

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