FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Circulation at Origin in Elliptical Lift Distribution Formula

GoCirculation at Origin given Induced Angle of Attack Formula

GoCirculation at Origin given Downwash Formula

Fx Copy

LaTeX Copy

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

Γ o = 2 \cdot V ∞ \cdot S 0 \cdot \frac{C l}{π \cdot b}

Γ_o - Circulation at Origin?V_∞ - Freestream Velocity?S₀ - Reference Area Origin?C_l - Lift Coefficient Origin?b - Wingspan?π - Archimedes' constant?

Circulation at Origin in Elliptical Lift Distribution Example

With values

With units

Only example

Here is how the Circulation at Origin in Elliptical Lift Distribution equation looks like with Values.

Here is how the Circulation at Origin in Elliptical Lift Distribution equation looks like with Units.

Here is how the Circulation at Origin in Elliptical Lift Distribution equation looks like.

13.9791 = 2 \cdot 15.5 \cdot 2.21 \cdot \frac{1.5}{3.1416 \cdot 2340}

13.9791m²/s = 2 \cdot 15.5m/s \cdot 2.21m² \cdot \frac{1.5}{3.1416 \cdot 2340mm}

13.9791 = 2 \cdot 15.5 \cdot 2.21 \cdot \frac{1.5}{3.1416 \cdot 2340}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aerodynamics » fx Circulation at Origin in Elliptical Lift Distribution

Circulation at Origin in Elliptical Lift Distribution Solution

Follow our step by step solution on how to calculate Circulation at Origin in Elliptical Lift Distribution?

FIRST Step Consider the formula

Γ o = 2 \cdot V ∞ \cdot S 0 \cdot \frac{C l}{π \cdot b}

Next Step Substitute values of Variables

∴

Γ o = 2 \cdot 15.5m/s \cdot 2.21m² \cdot \frac{1.5}{π \cdot 2340mm}

Next Step Substitute values of Constants

∴

Γ o = 2 \cdot 15.5m/s \cdot 2.21m² \cdot \frac{1.5}{3.1416 \cdot 2340mm}

Next Step Convert Units

∴

Γ o = 2 \cdot 15.5m/s \cdot 2.21m² \cdot \frac{1.5}{3.1416 \cdot 2.34m}

Next Step Prepare to Evaluate

∴

Γ o = 2 \cdot 15.5 \cdot 2.21 \cdot \frac{1.5}{3.1416 \cdot 2.34}

Next Step Evaluate

∴

Γ o = 13.9791091682381m²/s

LAST Step Rounding Answer

∴

Γ o = 13.9791m²/s

Circulation at Origin in Elliptical Lift Distribution Formula Elements

Variables

Constants

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

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

Reference Area Origin

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.

Symbol: S₀

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area Origin

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.

Symbol: C_l

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient Origin

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

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 to find Circulation at Origin

Go Circulation at Origin given Induced Angle of Attack

Γ o = 2 \cdot b \cdot α i \cdot V ∞

Go Circulation at Origin given Downwash

Γ o = - 2 \cdot w \cdot b

Go Circulation at Origin given Lift of Wing

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

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 Circulation at Origin in Elliptical Lift Distribution?

Circulation at Origin in Elliptical Lift Distribution evaluator uses Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan) to evaluate 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 evaluate Circulation at Origin in Elliptical Lift Distribution using this online evaluator? To use this online evaluator 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.

FAQs on Circulation at Origin in Elliptical Lift Distribution

What is the formula to find Circulation at Origin in Elliptical Lift Distribution?

The formula of Circulation at Origin in Elliptical Lift Distribution is expressed as Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan). Here is an example- 13.97911 = 2*15.5*2.21*1.5/(pi*2.34).

How to calculate Circulation at Origin in Elliptical Lift Distribution?

With Freestream Velocity (V_∞), Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b) we can find Circulation at Origin in Elliptical Lift Distribution using the formula - Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan). This formula also uses Archimedes' constant .

What are the other ways to Calculate Circulation at Origin?

Here are the different ways to Calculate Circulation at Origin-

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)

Can the Circulation at Origin in Elliptical Lift Distribution be negative?

Yes, the Circulation at Origin in Elliptical Lift Distribution, measured in Momentum Diffusivity can be negative.

Which unit is used to measure Circulation at Origin in Elliptical Lift Distribution?

Circulation at Origin in Elliptical Lift Distribution is usually measured using the Square Meter per Second[m²/s] for Momentum Diffusivity. Square Meter per Hour[m²/s], Square Centimeter per Second[m²/s] are the few other units in which Circulation at Origin in Elliptical Lift Distribution can be measured.

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Circulation at Origin in Elliptical Lift Distribution Formula

​GoCirculation at Origin given Induced Angle of Attack Formula

​GoCirculation at Origin given Downwash Formula

Circulation at Origin in Elliptical Lift Distribution Example

Circulation at Origin in Elliptical Lift Distribution Solution

Circulation at Origin in Elliptical Lift Distribution Formula Elements

Other Formulas to find Circulation at Origin

Other formulas in Elliptical Lift Distribution category

How to Evaluate Circulation at Origin in Elliptical Lift Distribution?

FAQs on Circulation at Origin in Elliptical Lift Distribution

Variable Name

GoCirculation at Origin given Induced Angle of Attack Formula

GoCirculation at Origin given Downwash Formula