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

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

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

Lift of Wing given Circulation at Origin Formula

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!