Induced Angle of Attack given Aspect Ratio Calculator

✖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%
✖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 Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack given Aspect Ratio [α_i]

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Induced Angle of Attack given Aspect Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)
α_i = C_l/(pi*AR_ELD)
This formula uses 1 Constants, 3 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.
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.
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

Lift Coefficient Origin: 1.5 --> No Conversion Required
Wing Aspect Ratio ELD: 2.48 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_i = C_l/(pi*AR_ELD) --> 1.5/(pi*2.48)

Evaluating ... ...

α_i = 0.19252614083697

STEP 3: Convert Result to Output's Unit

0.19252614083697 Radian -->11.0309353159018 Degree (Check conversion here)

FINAL ANSWER

11.0309353159018 ≈ 11.03094 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 Aspect Ratio Formula

LaTeX Go

Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)
α_i = C_l/(pi*AR_ELD)

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 Aspect Ratio?

Induced Angle of Attack given Aspect Ratio calculator uses Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD) to calculate the Induced Angle of Attack, The Induced angle of attack given aspect ratio 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 Aspect Ratio using this online calculator? To use this online calculator for Induced Angle of Attack given Aspect Ratio, enter Lift Coefficient Origin (C_l) & Wing Aspect Ratio ELD (AR_ELD) and hit the calculate button. Here is how the Induced Angle of Attack given Aspect Ratio calculation can be explained with given input values -> 870.7914 = 1.5/(pi*2.48).

FAQ

What is Induced Angle of Attack given Aspect Ratio?

The Induced angle of attack given aspect ratio formula calculates the angle between the direction of the freestream velocity and the local relative wind and is represented as α_i = C_l/(pi*AR_ELD) or Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD). 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 & 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 Induced Angle of Attack given Aspect Ratio?

The Induced angle of attack given aspect ratio formula calculates the angle between the direction of the freestream velocity and the local relative wind is calculated using Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD). To calculate Induced Angle of Attack given Aspect Ratio, you need Lift Coefficient Origin (C_l) & Wing Aspect Ratio ELD (AR_ELD). With our tool, you need to enter the respective value for Lift Coefficient Origin & 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 Induced Angle of Attack?

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

Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)
Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)
Induced Angle of Attack = -(Downwash/Freestream Velocity)

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