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Lift of Wing given Circulation at Origin Formula

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The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow. Check FAQs

F L = \frac{π \cdot ρ ∞ \cdot V ∞ \cdot b \cdot Γ o}{4}

F_L - Lift Force?ρ_∞ - Freestream Density?V_∞ - Freestream Velocity?b - Wingspan?Γ_o - Circulation at Origin?π - Archimedes' constant?

Lift of Wing given Circulation at Origin Example

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Here is how the Lift of Wing given Circulation at Origin equation looks like with Values.

Here is how the Lift of Wing given Circulation at Origin equation looks like with Units.

Here is how the Lift of Wing given Circulation at Origin equation looks like.

488.5416 = \frac{3.1416 \cdot 1.225 \cdot 15.5 \cdot 2340 \cdot 14}{4}

488.5416N = \frac{3.1416 \cdot 1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot 14m²/s}{4}

488.5416 = \frac{3.1416 \cdot 1.225 \cdot 15.5 \cdot 2340 \cdot 14}{4}

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Lift of Wing given Circulation at Origin Solution

Follow our step by step solution on how to calculate Lift of Wing given Circulation at Origin?

FIRST Step Consider the formula

F L = \frac{π \cdot ρ ∞ \cdot V ∞ \cdot b \cdot Γ o}{4}

Next Step Substitute values of Variables

∴

F L = \frac{π \cdot 1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot 14m²/s}{4}

Next Step Substitute values of Constants

∴

F L = \frac{3.1416 \cdot 1.225kg/m³ \cdot 15.5m/s \cdot 2340mm \cdot 14m²/s}{4}

Next Step Convert Units

∴

F L = \frac{3.1416 \cdot 1.225kg/m³ \cdot 15.5m/s \cdot 2.34m \cdot 14m²/s}{4}

Next Step Prepare to Evaluate

∴

F L = \frac{3.1416 \cdot 1.225 \cdot 15.5 \cdot 2.34 \cdot 14}{4}

Next Step Evaluate

∴

F L = 488.541612277196N

LAST Step Rounding Answer

∴

F L = 488.5416N

Lift of Wing given Circulation at Origin Formula Elements

Variables

Constants

Lift Force

The Lift Force is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.

Symbol: F_L

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Lift Force

Freestream Density

Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.

Symbol: ρ_∞

Measurement: DensityUnit: kg/m³

Note: Value can be positive or negative.

Formulas to find Freestream Density

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.

Symbol: V_∞

Measurement: SpeedUnit: m/s

Note: Value can be positive or negative.

Formulas to find Freestream Velocity

Wingspan

The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

Symbol: b

Measurement: LengthUnit: mm

Note: Value should be greater than 0.

Formulas to find Wingspan

Circulation at Origin

Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.

Symbol: Γ_o

Measurement: Momentum DiffusivityUnit: m²/s

Note: Value can be positive or negative.

Formulas to find Circulation at Origin

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

Other formulas in Elliptical Lift Distribution category

Go Circulation at given Distance along Wingspan

Γ = Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Lift at given Distance along Wingspan

L = ρ ∞ \cdot V ∞ \cdot Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Downwash in Elliptical Lift Distribution

w = - \frac{Γ o}{2 \cdot b}

Go Induced Angle of Attack given Aspect Ratio

α i = \frac{C l}{π \cdot AR ELD}

How to Evaluate Lift of Wing given Circulation at Origin?

Lift of Wing given Circulation at Origin evaluator uses Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4 to evaluate the Lift Force, The Lift of Wing given Circulation at Origin formula calculates the lift for the elliptical lift distribution along the wingspan when the circulation at the origin is given. Lift Force is denoted by F_L symbol.

How to evaluate Lift of Wing given Circulation at Origin using this online evaluator? To use this online evaluator for Lift of Wing given Circulation at Origin, enter Freestream Density (ρ_∞), Freestream Velocity (V_∞), Wingspan (b) & Circulation at Origin (Γ_o) and hit the calculate button.

FAQs on Lift of Wing given Circulation at Origin

What is the formula to find Lift of Wing given Circulation at Origin?

The formula of Lift of Wing given Circulation at Origin is expressed as Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4. Here is an example- 488.5416 = (pi*1.225*15.5*2.34*14)/4.

How to calculate Lift of Wing given Circulation at Origin?

With Freestream Density (ρ_∞), Freestream Velocity (V_∞), Wingspan (b) & Circulation at Origin (Γ_o) we can find Lift of Wing given Circulation at Origin using the formula - Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4. This formula also uses Archimedes' constant .

Can the Lift of Wing given Circulation at Origin be negative?

No, the Lift of Wing given Circulation at Origin, measured in Force cannot be negative.

Which unit is used to measure Lift of Wing given Circulation at Origin?

Lift of Wing given Circulation at Origin is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Lift of Wing given Circulation at Origin can be measured.

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Lift of Wing given Circulation at Origin Formula

Lift of Wing given Circulation at Origin Example

Lift of Wing given Circulation at Origin Solution

Lift of Wing given Circulation at Origin Formula Elements

Other formulas in Elliptical Lift Distribution category

How to Evaluate Lift of Wing given Circulation at Origin?

FAQs on Lift of Wing given Circulation at Origin

Variable Name