Coefficient of Lift given Induced Angle of Attack Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Lift Distribution

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Flow and Lift Distribution

Flow over Airfoils and Wings

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Elliptical Lift Distribution

General Lift Distribution

✖The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack [α_i]			+10% -10%
✖Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.ⓘ Wing Aspect Ratio ELD [AR_ELD]			+10% -10%

✖The Lift Coefficient ELD 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.ⓘ Coefficient of Lift given Induced Angle of Attack [C_L,ELD]

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Formula

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Coefficient of Lift given Induced Angle of Attack

Formula

`"C"_{"L,ELD"} = pi*"α"_{"i"}*"AR"_{"ELD"}`

Example

`"1.495793"=pi*"11°"*"2.48"`

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Coefficient of Lift given Induced Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD
C_L,ELD = pi*α_i*AR_ELD
This formula uses 1 Constants, 3 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Lift Coefficient ELD - The Lift Coefficient ELD 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.
Induced Angle of Attack - (Measured in Radian) - The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.
Wing Aspect Ratio ELD - Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.

STEP 1: Convert Input(s) to Base Unit

Induced Angle of Attack: 11 Degree --> 0.19198621771934 Radian (Check conversion here)
Wing Aspect Ratio ELD: 2.48 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,ELD = pi*α_i*AR_ELD --> pi*0.19198621771934*2.48

Evaluating ... ...

C_L,ELD = 1.49579337812037

STEP 3: Convert Result to Output's Unit

1.49579337812037 --> No Conversion Required

FINAL ANSWER

1.49579337812037 ≈ 1.495793 <-- Lift Coefficient ELD

(Calculation completed in 00.020 seconds)

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< 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

Coefficient of Lift given Induced Angle of Attack Formula

Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD
C_L,ELD = pi*α_i*AR_ELD

Why does drag coefficient increase with lift coefficient?

At low angles, the drag is nearly constant. The effect is called induced drag or drag due to lift. The flow around the wingtips of a finite wing creates an "induced" angle of attack on the wing near the tips. As the angle increases, the lift coefficient increases and this changes the amount of the induced drag.

How to Calculate Coefficient of Lift given Induced Angle of Attack?

Coefficient of Lift given Induced Angle of Attack calculator uses Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD to calculate the Lift Coefficient ELD, The Coefficient of lift given induced angle of attack formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing. Lift Coefficient ELD is denoted by C_L,ELD symbol.

How to calculate Coefficient of Lift given Induced Angle of Attack using this online calculator? To use this online calculator for Coefficient of Lift given Induced Angle of Attack, enter Induced Angle of Attack (α_i) & Wing Aspect Ratio ELD (AR_ELD) and hit the calculate button. Here is how the Coefficient of Lift given Induced Angle of Attack calculation can be explained with given input values -> 1.495793 = pi*0.19198621771934*2.48.

FAQ

What is Coefficient of Lift given Induced Angle of Attack?

The Coefficient of lift given induced angle of attack formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing and is represented as C_L,ELD = pi*α_i*AR_ELD or Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD. The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity & Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.

How to calculate Coefficient of Lift given Induced Angle of Attack?

The Coefficient of lift given induced angle of attack formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing is calculated using Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD. To calculate Coefficient of Lift given Induced Angle of Attack, you need Induced Angle of Attack (α_i) & Wing Aspect Ratio ELD (AR_ELD). With our tool, you need to enter the respective value for Induced Angle of Attack & Wing Aspect Ratio ELD and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Lift Coefficient ELD?

In this formula, Lift Coefficient ELD uses Induced Angle of Attack & Wing Aspect Ratio ELD. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin)
Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)

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