Aspect Ratio given Induced Angle of Attack Calculator

✖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.ⓘ Lift Coefficient ELD [C_L,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 [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.ⓘ Aspect Ratio given Induced Angle of Attack [AR_ELD]

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Aspect Ratio given Induced Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient ELD: 1.49 --> No Conversion Required
Induced Angle of Attack: 11 Degree --> 0.19198621771934 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

AR_ELD = C_L,ELD/(pi*α_i) --> 1.49/(pi*0.19198621771934)

Evaluating ... ...

AR_ELD = 2.47039467753456

STEP 3: Convert Result to Output's Unit

2.47039467753456 --> No Conversion Required

FINAL ANSWER

2.47039467753456 ≈ 2.470395 <-- Wing Aspect Ratio ELD

(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)

Aspect Ratio given Induced Angle of Attack Formula

LaTeX Go

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

How does aspect ratio affect aircraft performance?

The ratio of the length of wings to their width is called the aspect ratio. A high aspect ratio indicates long, narrow wings. Generally, high aspect ratio wings give slightly more lift and enable sustained, endurance flight, while low aspect ratio wings are best for swift maneuverability.

How to Calculate Aspect Ratio given Induced Angle of Attack?

Aspect Ratio given Induced Angle of Attack calculator uses Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack) to calculate the Wing Aspect Ratio ELD, The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift. Wing Aspect Ratio ELD is denoted by AR_ELD symbol.

How to calculate Aspect Ratio given Induced Angle of Attack using this online calculator? To use this online calculator for Aspect Ratio given Induced Angle of Attack, enter Lift Coefficient ELD (C_L,ELD) & Induced Angle of Attack (α_i) and hit the calculate button. Here is how the Aspect Ratio given Induced Angle of Attack calculation can be explained with given input values -> 2.486975 = 1.49/(pi*0.19198621771934).

FAQ

What is Aspect Ratio given Induced Angle of Attack?

The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift and is represented as AR_ELD = C_L,ELD/(pi*α_i) or Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack). 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 & The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

How to calculate Aspect Ratio given Induced Angle of Attack?

The Aspect ratio given induced angle of attack formula calculates the aspect ratio of the wing by using the induced angle of attack and the coefficient of lift is calculated using Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack). To calculate Aspect Ratio given Induced Angle of Attack, you need Lift Coefficient ELD (C_L,ELD) & Induced Angle of Attack (α_i). With our tool, you need to enter the respective value for Lift Coefficient ELD & Induced Angle of Attack 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 Wing Aspect Ratio ELD?

In this formula, Wing Aspect Ratio ELD uses Lift Coefficient ELD & Induced Angle of Attack. We can use 1 other way(s) to calculate the same, which is/are as follows -

Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)

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