Circulation at Origin given Lift of Wing Calculator

✖The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.ⓘ Lift Force [F_L]			+10% -10%
✖Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+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%
✖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 given Lift of Wing [Γ_o]

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Circulation at Origin given Lift of Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)
Γ_o = 4*F_L/(ρ_∞*V_∞*b*pi)
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.
Lift Force - (Measured in Newton) - The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
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.
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

Lift Force: 488.8 Newton --> 488.8 Newton No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Freestream Velocity: 15.5 Meter per Second --> 15.5 Meter per Second No Conversion Required
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Γ_o = 4*F_L/(ρ_∞*V_∞*b*pi) --> 4*488.8/(1.225*15.5*2.34*pi)

Evaluating ... ...

Γ_o = 14.0074045445226

STEP 3: Convert Result to Output's Unit

14.0074045445226 Square Meter per Second --> No Conversion Required

FINAL ANSWER

14.0074045445226 ≈ 14.0074 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 given Lift of Wing Formula

LaTeX Go

Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)
Γ_o = 4*F_L/(ρ_∞*V_∞*b*pi)

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 Lift of Wing?

Circulation at Origin given Lift of Wing calculator uses Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi) to calculate 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 calculate Circulation at Origin given Lift of Wing using this online calculator? To use this online calculator 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. Here is how the Circulation at Origin given Lift of Wing calculation can be explained with given input values -> 14.0074 = 4*488.8/(1.225*15.5*2.34*pi).

FAQ

What is Circulation at Origin given Lift of Wing?

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 and is represented as Γ_o = 4*F_L/(ρ_∞*V_∞*b*pi) or Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi). The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow, Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, 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 & 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 given Lift of Wing?

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 is calculated using Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi). To calculate Circulation at Origin given Lift of Wing, you need Lift Force (F_L), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Wingspan (b). With our tool, you need to enter the respective value for Lift Force, Freestream Density, Freestream Velocity & 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 Lift Force, Freestream Density, Freestream Velocity & Wingspan. 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*Wingspan*Induced Angle of Attack*Freestream Velocity
Circulation at Origin = -2*Downwash*Wingspan

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