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
FL = (pi*ρ*V*b*Γo)/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
FL = (pi*ρ*V*b*Γo)/4 --> (pi*1.225*15.5*2.34*14)/4
Evaluating ... ...
FL = 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 00.004 seconds)

Credits

Creator Image
Created by Ravi Khiyani
Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore
Ravi Khiyani has created this Calculator and 200+ more calculators!
Verifier Image
Verified by Anshika Arya
National Institute Of Technology (NIT), Hamirpur
Anshika Arya has verified this Calculator and 2500+ more calculators!

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
FL = (pi*ρ*V*b*Γo)/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 FL 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 ), Freestream Velocity (V), Wingspan (b) & Circulation at Origin 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 FL = (pi*ρ*V*b*Γo)/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 ), Freestream Velocity (V), Wingspan (b) & Circulation at Origin 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.
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!