Induced Angle of Attack given Coefficient of Lift Calculator

✖Reference Area Origin is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area.ⓘ Reference Area Origin [S₀]			+10% -10%
✖Lift Coefficient Origin 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.ⓘ Lift Coefficient Origin [C_l]			+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 Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack given Coefficient of Lift [α_i]

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Induced Angle of Attack given Coefficient of Lift Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)
α_i = S₀*C_l/(pi*b^2)
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
Reference Area Origin - (Measured in Square Meter) - Reference Area Origin is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area.
Lift Coefficient Origin - Lift Coefficient Origin 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.
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

Reference Area Origin: 2.21 Square Meter --> 2.21 Square Meter No Conversion Required
Lift Coefficient Origin: 1.5 --> No Conversion Required
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_i = S₀*C_l/(pi*b^2) --> 2.21*1.5/(pi*2.34^2)

Evaluating ... ...

α_i = 0.192708976678221

STEP 3: Convert Result to Output's Unit

0.192708976678221 Radian -->11.0414110379491 Degree (Check conversion here)

FINAL ANSWER

11.0414110379491 ≈ 11.04141 Degree <-- Induced Angle of Attack

(Calculation completed in 00.004 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)

Induced Angle of Attack given Coefficient of Lift Formula

LaTeX Go

Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)
α_i = S₀*C_l/(pi*b^2)

How does angle of attack affect the airfoil?

An increase in the angle of attack results in an increase in both lift and induced drag, up to a point. Too high an angle of attack (usually around 17 degrees) and the airflow across the upper surface of the aerofoil become detached, resulting in a loss of lift, otherwise known as a Stall.

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

Induced Angle of Attack given Coefficient of Lift calculator uses Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2) to calculate the Induced Angle of Attack, The Induced angle of attack given coefficient of lift formula calculates the angle between the direction of the freestream velocity and the local relative wind. Induced Angle of Attack is denoted by α_i symbol.

How to calculate Induced Angle of Attack given Coefficient of Lift using this online calculator? To use this online calculator for Induced Angle of Attack given Coefficient of Lift, enter Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b) and hit the calculate button. Here is how the Induced Angle of Attack given Coefficient of Lift calculation can be explained with given input values -> 632.6263 = 2.21*1.5/(pi*2.34^2).

FAQ

What is Induced Angle of Attack given Coefficient of Lift?

The Induced angle of attack given coefficient of lift formula calculates the angle between the direction of the freestream velocity and the local relative wind and is represented as α_i = S₀*C_l/(pi*b^2) or Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2). Reference Area Origin is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area, Lift Coefficient Origin 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 & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

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

The Induced angle of attack given coefficient of lift formula calculates the angle between the direction of the freestream velocity and the local relative wind is calculated using Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2). To calculate Induced Angle of Attack given Coefficient of Lift, you need Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b). With our tool, you need to enter the respective value for Reference Area Origin, Lift Coefficient Origin & Wingspan 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 Induced Angle of Attack?

In this formula, Induced Angle of Attack uses Reference Area Origin, Lift Coefficient Origin & Wingspan. We can use 3 other way(s) to calculate the same, which is/are as follows -

Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)
Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)
Induced Angle of Attack = -(Downwash/Freestream Velocity)

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