Induced Lift Slope Factor given Lift Curve Slope of Finite Wing Calculator

✖Wing Aspect Ratio GLD 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 GLD [AR_GLD]			+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 [a₀]			+10% -10%
✖The lift curve slope is a measure of how rapidly the wing generates lift with a change in angle of attack.ⓘ Lift Curve Slope [a_C,l]			+10% -10%

✖The Induced Lift Slope Factor of Finite Wing 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 given Lift Curve Slope of Finite Wing [τ_FW]

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Induced Lift Slope Factor given Lift Curve Slope of Finite Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1
τ_FW = (pi*AR_GLD*(a₀/a_C,l-1))/a₀-1
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Induced Lift Slope Factor of Finite Wing - The Induced Lift Slope Factor of Finite Wing 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 GLD - Wing Aspect Ratio GLD 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 angle of attack.

STEP 1: Convert Input(s) to Base Unit

Wing Aspect Ratio GLD: 15 --> No Conversion Required
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

τ_FW = (pi*AR_GLD*(a₀/a_C,l-1))/a₀-1 --> (pi*15*(6.28/5.54-1))/6.28-1

Evaluating ... ...

τ_FW = 0.00231318422034121

STEP 3: Convert Result to Output's Unit

0.00231318422034121 --> No Conversion Required

FINAL ANSWER

0.00231318422034121 ≈ 0.002313 <-- Induced Lift Slope Factor of Finite Wing

(Calculation completed in 00.004 seconds)

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< General Lift Distribution Calculators

Lift Coefficient given Span Efficiency Factor

LaTeX Go Lift Coefficient GLD = sqrt(pi*Span Efficiency Factor*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)

Induced Drag Coefficient given Span Efficiency Factor

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

Span Efficiency Factor

LaTeX Go Span Efficiency Factor = (1+Induced Drag Factor)^(-1)

Induced Drag Factor given Span Efficiency Factor

LaTeX Go Induced Drag Factor = Span Efficiency Factor^(-1)-1

Induced Lift Slope Factor given Lift Curve Slope of Finite Wing Formula

LaTeX Go

Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1
τ_FW = (pi*AR_GLD*(a₀/a_C,l-1))/a₀-1

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 Induced Lift Slope Factor given Lift Curve Slope of Finite Wing?

Induced Lift Slope Factor given Lift Curve Slope of Finite Wing calculator uses Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1 to calculate the Induced Lift Slope Factor of Finite Wing, The Induced Lift Slope Factor given Lift Curve Slope of Finite Wing formula calculates the induced lift slope factor which is a function of the Fourier coefficients which is used for the lift curve slope expression for the finite wing of the general planform. Induced Lift Slope Factor of Finite Wing is denoted by τ_FW symbol.

How to calculate Induced Lift Slope Factor given Lift Curve Slope of Finite Wing using this online calculator? To use this online calculator for Induced Lift Slope Factor given Lift Curve Slope of Finite Wing, enter Wing Aspect Ratio GLD (AR_GLD), 2D Lift Curve Slope (a₀) & Lift Curve Slope (a_C,l) and hit the calculate button. Here is how the Induced Lift Slope Factor given Lift Curve Slope of Finite Wing calculation can be explained with given input values -> 0.002313 = (pi*15*(6.28/5.54-1))/6.28-1.

FAQ

What is Induced Lift Slope Factor given Lift Curve Slope of Finite Wing?

The Induced Lift Slope Factor given Lift Curve Slope of Finite Wing formula calculates the induced lift slope factor which is a function of the Fourier coefficients which is used for the lift curve slope expression for the finite wing of the general planform and is represented as τ_FW = (pi*AR_GLD*(a₀/a_C,l-1))/a₀-1 or Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1. Wing Aspect Ratio GLD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform, 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 angle of attack.

How to calculate Induced Lift Slope Factor given Lift Curve Slope of Finite Wing?

The Induced Lift Slope Factor given Lift Curve Slope of Finite Wing formula calculates the induced lift slope factor which is a function of the Fourier coefficients which is used for the lift curve slope expression for the finite wing of the general planform is calculated using Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1. To calculate Induced Lift Slope Factor given Lift Curve Slope of Finite Wing, you need Wing Aspect Ratio GLD (AR_GLD), 2D Lift Curve Slope (a₀) & Lift Curve Slope (a_C,l). With our tool, you need to enter the respective value for Wing Aspect Ratio GLD, 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.

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