Lift of Wing given Circulation at Origin Calculator

✖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 [Γ_o]			+10% -10%

✖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 of Wing given Circulation at Origin [F_L]

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Lift of Wing given Circulation at Origin Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4
F_L = (pi*ρ_∞*V_∞*b*Γ_o)/4
This formula uses 1 Constants, 5 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

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)
Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_L = (pi*ρ_∞*V_∞*b*Γ_o)/4 --> (pi*1.225*15.5*2.34*14)/4

Evaluating ... ...

F_L = 488.541612277196

STEP 3: Convert Result to Output's Unit

488.541612277196 Newton --> No Conversion Required

FINAL ANSWER

488.541612277196 ≈ 488.5416 Newton <-- Lift Force

(Calculation completed in 00.020 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)

Lift of Wing given Circulation at Origin Formula

LaTeX Go

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

Why is an elliptical lift distribution ideal?

The energy in that vortex appears to the aircraft as 'lift induced drag'. The aerodynamicist tries to design the tip to keep induced drag low. An elliptical lift distribution is best for this purpose. The shape producing this varies with speed, altitude, and other factors, so tips vary from design to design.

How to Calculate Lift of Wing given Circulation at Origin?

Lift of Wing given Circulation at Origin calculator uses Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4 to calculate 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 calculate Lift of Wing given Circulation at Origin using this online calculator? To use this online calculator 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. Here is how the Lift of Wing given Circulation at Origin calculation can be explained with given input values -> 488.5416 = (pi*1.225*15.5*2.34*14)/4.

FAQ

What is Lift of Wing given Circulation at Origin?

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 and is represented as F_L = (pi*ρ_∞*V_∞*b*Γ_o)/4 or Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4. 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 & Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.

How to calculate Lift of Wing given Circulation at Origin?

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