Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing Calculator

✖The 2D Lift Curve Slope is a measure of how rapidly the airfoil generates lift with a change in angle of attack.ⓘ 2D Lift Curve Slope [a₀]			+10% -10%
✖The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack.ⓘ Lift Curve Slope [a_C,l]			+10% -10%

✖Wing Aspect Ratio 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 of Wing given Lift Curve Slope of Elliptic Finite Wing [AR]

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Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Aspect Ratio = 2D Lift Curve Slope/(pi*(2D Lift Curve Slope/Lift Curve Slope-1))
AR = a₀/(pi*(a₀/a_C,l-1))
This formula uses 1 Constants, 3 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Wing Aspect Ratio - Wing Aspect Ratio is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.
2D Lift Curve Slope - (Measured in 1 per Radian) - The 2D Lift Curve Slope is a measure of how rapidly the airfoil generates lift with a change in angle of attack.
Lift Curve Slope - (Measured in 1 per Radian) - The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack.

STEP 1: Convert Input(s) to Base Unit

2D Lift Curve Slope: 6.28 1 per Radian --> 6.28 1 per Radian No Conversion Required
Lift Curve Slope: 5.54 1 per Radian --> 5.54 1 per Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

AR = a₀/(pi*(a₀/a_C,l-1)) --> 6.28/(pi*(6.28/5.54-1))

Evaluating ... ...

AR = 14.9653823137804

STEP 3: Convert Result to Output's Unit

14.9653823137804 --> No Conversion Required

FINAL ANSWER

14.9653823137804 ≈ 14.96538 <-- Wing Aspect Ratio

(Calculation completed in 00.004 seconds)

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< Flow over Wings Calculators

2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing

LaTeX Go 2D Lift Curve Slope = Lift Curve Slope/(1-(Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio))

Aspect Ratio given Span Efficiency Factor

LaTeX Go Wing Aspect Ratio = Lift Coefficient^2/(pi*Span Efficiency Factor*Induced Drag Coefficient)

2D Lift Curve Slope of Airfoil given Lift Slope of Elliptic Finite Wing

LaTeX Go 2D Lift Curve Slope = Lift Curve Slope/(1-Lift Curve Slope/(pi*Wing Aspect Ratio))

Effective Angle of Attack of Finite Wing

LaTeX Go Effective Angle of Attack = Geometric Angle of Attack-Induced Angle of Attack

Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing Formula

LaTeX Go

Wing Aspect Ratio = 2D Lift Curve Slope/(pi*(2D Lift Curve Slope/Lift Curve Slope-1))
AR = a₀/(pi*(a₀/a_C,l-1))

How does aspect ratio affect aircraft?

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 of Wing given Lift Curve Slope of Elliptic Finite Wing?

Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing calculator uses Wing Aspect Ratio = 2D Lift Curve Slope/(pi*(2D Lift Curve Slope/Lift Curve Slope-1)) to calculate the Wing Aspect Ratio, The Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the lift curve slope of the elliptic finite wing. Wing Aspect Ratio is denoted by AR symbol.

How to calculate Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing using this online calculator? To use this online calculator for Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing, enter 2D Lift Curve Slope (a₀) & Lift Curve Slope (a_C,l) and hit the calculate button. Here is how the Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing calculation can be explained with given input values -> 14.96538 = 6.28/(pi*(6.28/5.54-1)).

FAQ

What is Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing?

The Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the lift curve slope of the elliptic finite wing and is represented as AR = a₀/(pi*(a₀/a_C,l-1)) or Wing Aspect Ratio = 2D Lift Curve Slope/(pi*(2D Lift Curve Slope/Lift Curve Slope-1)). The 2D Lift Curve Slope is a measure of how rapidly the airfoil generates lift with a change in angle of attack & The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack.

How to calculate Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing?

The Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing formula calculates the aspect ratio of the wing for the actual lift distribution which is a function of the Fourier series, by using the lift curve slope of the elliptic finite wing is calculated using Wing Aspect Ratio = 2D Lift Curve Slope/(pi*(2D Lift Curve Slope/Lift Curve Slope-1)). To calculate Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing, you need 2D Lift Curve Slope (a₀) & Lift Curve Slope (a_C,l). With our tool, you need to enter the respective value for 2D Lift Curve Slope & Lift Curve Slope 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?

In this formula, Wing Aspect Ratio uses 2D Lift Curve Slope & Lift Curve Slope. We can use 2 other way(s) to calculate the same, which is/are as follows -

Wing Aspect Ratio = Lift Coefficient^2/(pi*Span Efficiency Factor*Induced Drag Coefficient)
Wing Aspect Ratio = (2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*(2D Lift Curve Slope/Lift Curve Slope-1))

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