Circulation at given Distance along Wingspan 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

✖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%
✖Distance from center to point is the length of line segment measured from the center of a body to a particular point.ⓘ Distance from Center to Point [a]			+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 is a scalar integral quantity, is a macroscopic measure of rotation for a finite area of the fluid.ⓘ Circulation at given Distance along Wingspan [Γ]

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Formula

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Circulation at given Distance along Wingspan

Formula

`"Γ" = "Γ"_{"o"}*sqrt(1-(2*"a"/"b")^2)`

Example

`"13.99862m²/s"="14m²/s"*sqrt(1-(2*"16.4mm"/"2340mm")^2)`

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Download Elliptical Lift Distribution Formulas PDF

Circulation at given Distance along Wingspan Solution

STEP 0: Pre-Calculation Summary

Formula Used

Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)
Γ = Γ_o*sqrt(1-(2*a/b)^2)
This formula uses 1 Functions, 4 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Circulation - (Measured in Square Meter per Second) - Circulation is a scalar integral quantity, is a macroscopic measure of rotation for a finite area of the fluid.
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.
Distance from Center to Point - (Measured in Meter) - Distance from center to point is the length of line segment measured from the center of a body to a particular point.
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

Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required
Distance from Center to Point: 16.4 Millimeter --> 0.0164 Meter (Check conversion here)
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Γ = Γ_o*sqrt(1-(2*a/b)^2) --> 14*sqrt(1-(2*0.0164/2.34)^2)

Evaluating ... ...

Γ = 13.9986245799636

STEP 3: Convert Result to Output's Unit

13.9986245799636 Square Meter per Second --> No Conversion Required

FINAL ANSWER

13.9986245799636 ≈ 13.99862 Square Meter per Second <-- Circulation

(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 given Distance along Wingspan Formula

Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)
Γ = Γ_o*sqrt(1-(2*a/b)^2)

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 given Distance along Wingspan?

Circulation at given Distance along Wingspan calculator uses Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2) to calculate the Circulation, The Circulation at given Distance along Wingspan formula calculates the circulation at a particular point along the wingspan which is at a given distance from the center of the bound vortex or the considered origin. Circulation is denoted by Γ symbol.

How to calculate Circulation at given Distance along Wingspan using this online calculator? To use this online calculator for Circulation at given Distance along Wingspan, enter Circulation at Origin (Γ_o), Distance from Center to Point (a) & Wingspan (b) and hit the calculate button. Here is how the Circulation at given Distance along Wingspan calculation can be explained with given input values -> 13.99862 = 14*sqrt(1-(2*0.0164/2.34)^2).

FAQ

What is Circulation at given Distance along Wingspan?

The Circulation at given Distance along Wingspan formula calculates the circulation at a particular point along the wingspan which is at a given distance from the center of the bound vortex or the considered origin and is represented as Γ = Γ_o*sqrt(1-(2*a/b)^2) or Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2). Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex, Distance from center to point is the length of line segment measured from the center of a body to a particular point & 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 given Distance along Wingspan?

The Circulation at given Distance along Wingspan formula calculates the circulation at a particular point along the wingspan which is at a given distance from the center of the bound vortex or the considered origin is calculated using Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2). To calculate Circulation at given Distance along Wingspan, you need Circulation at Origin (Γ_o), Distance from Center to Point (a) & Wingspan (b). With our tool, you need to enter the respective value for Circulation at Origin, Distance from Center to Point & Wingspan and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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