Coefficient of Lift given Circulation at Origin 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%
✖Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.ⓘ Circulation at Origin [Γ_o]			+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%
✖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%

✖The Lift Coefficient ELD 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.ⓘ Coefficient of Lift given Circulation at Origin [C_L,ELD]

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Coefficient of Lift given Circulation at Origin Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Lift Coefficient ELD - The Lift Coefficient ELD 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.
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.

STEP 1: Convert Input(s) to Base Unit

Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)
Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required
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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,ELD = pi*b*Γ_o/(2*V_∞*S₀) --> pi*2.34*14/(2*15.5*2.21)

Evaluating ... ...

C_L,ELD = 1.50224164839588

STEP 3: Convert Result to Output's Unit

1.50224164839588 --> No Conversion Required

FINAL ANSWER

1.50224164839588 ≈ 1.502242 <-- Lift Coefficient ELD

(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)

Coefficient of Lift given Circulation at Origin Formula

LaTeX Go

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

Why does drag coefficient increase with lift coefficient?

At low angles, the drag is nearly constant. The effect is called induced drag or drag due to lift. The flow around the wingtips of a finite wing creates an "induced" angle of attack on the wing near the tips. As the angle increases, the lift coefficient increases and this changes the amount of the induced drag.

How to Calculate Coefficient of Lift given Circulation at Origin?

Coefficient of Lift given Circulation at Origin calculator uses Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin) to calculate the Lift Coefficient ELD, The Coefficient of Lift given Circulation at Origin formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing. Lift Coefficient ELD is denoted by C_L,ELD symbol.

How to calculate Coefficient of Lift given Circulation at Origin using this online calculator? To use this online calculator for Coefficient of Lift given Circulation at Origin, enter Wingspan (b), Circulation at Origin (Γ_o), Freestream Velocity (V_∞) & Reference Area Origin (S₀) and hit the calculate button. Here is how the Coefficient of Lift given Circulation at Origin calculation can be explained with given input values -> 1.502242 = pi*2.34*14/(2*15.5*2.21).

FAQ

What is Coefficient of Lift given Circulation at Origin?

The Coefficient of Lift given Circulation at Origin formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing and is represented as C_L,ELD = pi*b*Γ_o/(2*V_∞*S₀) or Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin). The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex, 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.

How to calculate Coefficient of Lift given Circulation at Origin?

The Coefficient of Lift given Circulation at Origin formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing is calculated using Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin). To calculate Coefficient of Lift given Circulation at Origin, you need Wingspan (b), Circulation at Origin (Γ_o), Freestream Velocity (V_∞) & Reference Area Origin (S₀). With our tool, you need to enter the respective value for Wingspan, Circulation at Origin, Freestream Velocity & Reference Area Origin 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 Lift Coefficient ELD?

In this formula, Lift Coefficient ELD uses Wingspan, Circulation at Origin, Freestream Velocity & Reference Area Origin. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)
Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD

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