Lift at given Distance along Wingspan 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%
✖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%
✖Distance from center to point is the length of line segment measured from the center of a body to a particular point.ⓘ Distance from Center to Point [a]			+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%

✖The Lift at Distance is the sum of all the forces at that point which causes it to move perpendicular to the direction of flow.ⓘ Lift at given Distance along Wingspan [L]

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Lift at given Distance along Wingspan Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)
L = ρ_∞*V_∞*Γ_o*sqrt(1-(2*a/b)^2)
This formula uses 1 Functions, 6 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Lift at Distance - (Measured in Newton) - The Lift at Distance is the sum of all the forces at that point which causes 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.
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.
Distance from Center to Point - (Measured in Meter) - Distance from center to point is the length of line segment measured from the center of a body to a particular point.
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.

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
Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required
Distance from Center to Point: 16.4 Millimeter --> 0.0164 Meter (Check conversion here)
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L = ρ_∞*V_∞*Γ_o*sqrt(1-(2*a/b)^2) --> 1.225*15.5*14*sqrt(1-(2*0.0164/2.34)^2)

Evaluating ... ...

L = 265.798884212059

STEP 3: Convert Result to Output's Unit

265.798884212059 Newton --> No Conversion Required

FINAL ANSWER

265.798884212059 ≈ 265.7989 Newton <-- Lift at Distance

(Calculation completed in 00.004 seconds)

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Created by Ravi Khiyani

Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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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 at given Distance along Wingspan Formula

LaTeX Go

Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)
L = ρ_∞*V_∞*Γ_o*sqrt(1-(2*a/b)^2)

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 at given Distance along Wingspan?

Lift at given Distance along Wingspan calculator uses Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2) to calculate the Lift at Distance, The Lift at given Distance along Wingspan formula calculates the lift for the elliptical lift distribution along the wingspan at the given point from the center of the elliptical distribution. Lift at Distance is denoted by L symbol.

How to calculate Lift at given Distance along Wingspan using this online calculator? To use this online calculator for Lift at given Distance along Wingspan, enter Freestream Density (ρ_∞), Freestream Velocity (V_∞), Circulation at Origin (Γ_o), Distance from Center to Point (a) & Wingspan (b) and hit the calculate button. Here is how the Lift at given Distance along Wingspan calculation can be explained with given input values -> 265.7989 = 1.225*15.5*14*sqrt(1-(2*0.0164/2.34)^2).

FAQ

What is Lift at given Distance along Wingspan?

The Lift at given Distance along Wingspan formula calculates the lift for the elliptical lift distribution along the wingspan at the given point from the center of the elliptical distribution and is represented as L = ρ_∞*V_∞*Γ_o*sqrt(1-(2*a/b)^2) or Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2). 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, Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex, Distance from center to point is the length of line segment measured from the center of a body to a particular point & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

How to calculate Lift at given Distance along Wingspan?

The Lift at given Distance along Wingspan formula calculates the lift for the elliptical lift distribution along the wingspan at the given point from the center of the elliptical distribution is calculated using Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2). To calculate Lift at given Distance along Wingspan, you need Freestream Density (ρ_∞), Freestream Velocity (V_∞), Circulation at Origin (Γ_o), Distance from Center to Point (a) & Wingspan (b). With our tool, you need to enter the respective value for Freestream Density, Freestream Velocity, Circulation at Origin, Distance from Center to Point & Wingspan 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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