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
τFW = (pi*ARGLD*(a0/aC,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
τFW = (pi*ARGLD*(a0/aC,l-1))/a0-1 --> (pi*15*(6.28/5.54-1))/6.28-1
Evaluating ... ...
τFW = 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 00.020 seconds)

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10+ General Lift Distribution Calculators

Induced Lift Slope Factor given Lift Curve Slope of Finite Wing
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
Lift Coefficient given Induced Drag Factor
Go Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor))
Lift Coefficient given Span Efficiency Factor
Go Lift Coefficient GLD = sqrt(pi*Span Efficiency Factor*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)
Induced Drag Coefficient given Induced Drag Factor
Go Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD)
Aspect Ratio given Induced Drag Factor
Go Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD)
Induced Drag Coefficient given Span Efficiency Factor
Go Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD)
Span Efficiency Factor given Induced Drag Coefficient
Go Span Efficiency Factor = Lift Coefficient GLD^2/(pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)
Induced Drag Factor given Induced Drag Coefficient
Go Induced Drag Factor = (pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/Lift Coefficient GLD^2-1
Span Efficiency Factor
Go Span Efficiency Factor = (1+Induced Drag Factor)^(-1)
Induced Drag Factor given Span Efficiency Factor
Go Induced Drag Factor = Span Efficiency Factor^(-1)-1

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

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
τFW = (pi*ARGLD*(a0/aC,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 τFW 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 (ARGLD), 2D Lift Curve Slope (a0) & Lift Curve Slope (aC,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 τFW = (pi*ARGLD*(a0/aC,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 (ARGLD), 2D Lift Curve Slope (a0) & Lift Curve Slope (aC,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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