Lift Curve Slope for 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 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 Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack.ⓘ Lift Curve Slope for Finite Wing [a_C,l]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Flow over Airfoils and Wings Formulas PDF PDF Image

Lift Curve Slope for Finite Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
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.
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

2D Lift Curve Slope: 6.28 1 per Radian --> 6.28 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

a_C,l = a₀/(1+(a₀*(1+τ))/(pi*AR)) --> 6.28/(1+(6.28*(1+0.055))/(pi*15))

Evaluating ... ...

a_C,l = 5.50589652529656

STEP 3: Convert Result to Output's Unit

5.50589652529656 1 per Radian --> No Conversion Required

FINAL ANSWER

5.50589652529656 ≈ 5.505897 1 per Radian <-- Lift Curve Slope

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aerodynamics » Two Dimensional Incompressible Flow » Flow over Airfoils and Wings » Aerospace » Flow over Wings » Lift Curve Slope for Finite Wing

Credits

Created by Ravi Khiyani

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

Ravi Khiyani has created this Calculator and 200+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 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

Lift Curve Slope for Finite Wing Formula

LaTeX Go

Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio))
a_C,l = a₀/(1+(a₀*(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 Lift Curve Slope for Finite Wing?

Lift Curve Slope for Finite Wing calculator uses Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)) to calculate the Lift Curve Slope, The Lift Curve Slope for Finite Wing formula calculates the rate at which lift coefficient changes with angle of attack for a finite wing. Lift Curve Slope is denoted by a_C,l symbol.

How to calculate Lift Curve Slope for Finite Wing using this online calculator? To use this online calculator for Lift Curve Slope for Finite Wing, enter 2D Lift Curve Slope (a₀), Induced Lift Slope Factor (τ) & Wing Aspect Ratio (AR) and hit the calculate button. Here is how the Lift Curve Slope for Finite Wing calculation can be explained with given input values -> 5.505897 = 6.28/(1+(6.28*(1+0.055))/(pi*15)).

FAQ

What is Lift Curve Slope for Finite Wing?

The Lift Curve Slope for Finite Wing formula calculates the rate at which lift coefficient changes with angle of attack for a finite wing and is represented as a_C,l = a₀/(1+(a₀*(1+τ))/(pi*AR)) or Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). The 2D Lift Curve Slope is a measure of how rapidly the airfoil generates lift with a change in 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 Lift Curve Slope for Finite Wing?

The Lift Curve Slope for Finite Wing formula calculates the rate at which lift coefficient changes with angle of attack for a finite wing is calculated using Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). To calculate Lift Curve Slope for Finite Wing, you need 2D Lift Curve Slope (a₀), Induced Lift Slope Factor (τ) & Wing Aspect Ratio (AR). With our tool, you need to enter the respective value for 2D 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 Lift Curve Slope?

In this formula, Lift Curve Slope uses 2D 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 -

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

Home

FREE PDFs

🔍 Search