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

✖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%
✖The Induced Lift Slope Factor is a function of the Fourier coefficients which have been used for the lift curve slope expression for the finite wing of the general planform.ⓘ Induced Lift Slope Factor [τ]			+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.ⓘ Wing Aspect Ratio [AR]			+10% -10%

✖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 of Airfoil given Lift Slope of Finite Wing [a₀]

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

STEP 0: Pre-Calculation Summary

Formula Used

2D Lift Curve Slope = Lift Curve Slope/(1-(Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio))
a₀ = a_C,l/(1-(a_C,l*(1+τ))/(pi*AR))
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
Induced Lift Slope Factor - The Induced Lift Slope Factor is a function of the Fourier coefficients which have been used for the lift curve slope expression for the finite wing of the general planform.
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.

STEP 1: Convert Input(s) to Base Unit

Lift Curve Slope: 5.54 1 per Radian --> 5.54 1 per Radian No Conversion Required
Induced Lift Slope Factor: 0.055 --> No Conversion Required
Wing Aspect Ratio: 15 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

a₀ = a_C,l/(1-(a_C,l*(1+τ))/(pi*AR)) --> 5.54/(1-(5.54*(1+0.055))/(pi*15))

Evaluating ... ...

a₀ = 6.32440585083825

STEP 3: Convert Result to Output's Unit

6.32440585083825 1 per Radian --> No Conversion Required

FINAL ANSWER

6.32440585083825 ≈ 6.324406 1 per Radian <-- 2D Lift Curve Slope

(Calculation completed in 00.004 seconds)

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Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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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

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

LaTeX Go

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

What does camber do to the lift curve slope?

The effect of increasing the airfoil camber causes a greater differential change in momentum of the flow around the airfoil, which causes differences in the pressure difference, thus increasing lift. However, the trade-off is that an increase in the camber of the flat plate also increases drag.

How to Calculate 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing?

2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing calculator uses 2D Lift Curve Slope = Lift Curve Slope/(1-(Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)) to calculate the 2D Lift Curve Slope, The 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing formula calculates the lift curve slope of an airfoil used for the finite wing of the general platform by using the lift curve slope of the finite or 3D wing. 2D Lift Curve Slope is denoted by a₀ symbol.

How to calculate 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing using this online calculator? To use this online calculator for 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing, enter Lift Curve Slope (a_C,l), Induced Lift Slope Factor (τ) & Wing Aspect Ratio (AR) and hit the calculate button. Here is how the 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing calculation can be explained with given input values -> 6.324406 = 5.54/(1-(5.54*(1+0.055))/(pi*15)).

FAQ

What is 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing?

The 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing formula calculates the lift curve slope of an airfoil used for the finite wing of the general platform by using the lift curve slope of the finite or 3D wing and is represented as a₀ = a_C,l/(1-(a_C,l*(1+τ))/(pi*AR)) or 2D Lift Curve Slope = Lift Curve Slope/(1-(Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack, The Induced Lift Slope Factor is a function of the Fourier coefficients which have been used for the lift curve slope expression for the finite wing of the general planform & 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.

How to calculate 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing?

The 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing formula calculates the lift curve slope of an airfoil used for the finite wing of the general platform by using the lift curve slope of the finite or 3D wing is calculated using 2D Lift Curve Slope = Lift Curve Slope/(1-(Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). To calculate 2D Lift Curve Slope of Airfoil given Lift Slope of Finite Wing, you need Lift Curve Slope (a_C,l), Induced Lift Slope Factor (τ) & Wing Aspect Ratio (AR). With our tool, you need to enter the respective value for Lift Curve Slope, Induced Lift Slope Factor & Wing Aspect Ratio 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 2D Lift Curve Slope?

In this formula, 2D Lift Curve Slope uses Lift Curve Slope, Induced Lift Slope Factor & Wing Aspect Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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