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Lift Curve Slope for Finite Wing Formula

GoLift Curve Slope for Elliptic Finite Wing Formula

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The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack. Check FAQs

a C,l = \frac{a 0}{1 + \frac{a 0 \cdot (1 + τ)}{π \cdot AR}}

a_C,l - Lift Curve Slope?a₀ - 2D Lift Curve Slope?τ - Induced Lift Slope Factor?AR - Wing Aspect Ratio?π - Archimedes' constant?

Lift Curve Slope for Finite Wing Example

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Here is how the Lift Curve Slope for Finite Wing equation looks like with Values.

Here is how the Lift Curve Slope for Finite Wing equation looks like with Units.

Here is how the Lift Curve Slope for Finite Wing equation looks like.

5.5059 = \frac{6.28}{1 + \frac{6.28 \cdot (1 + 0.055)}{3.1416 \cdot 15}}

5.5059rad⁻¹ = \frac{6.28rad⁻¹}{1 + \frac{6.28rad⁻¹ \cdot (1 + 0.055)}{3.1416 \cdot 15}}

5.5059 = \frac{6.28}{1 + \frac{6.28 \cdot (1 + 0.055)}{3.1416 \cdot 15}}

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Lift Curve Slope for Finite Wing Solution

Follow our step by step solution on how to calculate Lift Curve Slope for Finite Wing?

FIRST Step Consider the formula

a C,l = \frac{a 0}{1 + \frac{a 0 \cdot (1 + τ)}{π \cdot AR}}

Next Step Substitute values of Variables

∴

a C,l = \frac{6.28rad⁻¹}{1 + \frac{6.28rad⁻¹ \cdot (1 + 0.055)}{π \cdot 15}}

Next Step Substitute values of Constants

∴

a C,l = \frac{6.28rad⁻¹}{1 + \frac{6.28rad⁻¹ \cdot (1 + 0.055)}{3.1416 \cdot 15}}

Next Step Prepare to Evaluate

∴

a C,l = \frac{6.28}{1 + \frac{6.28 \cdot (1 + 0.055)}{3.1416 \cdot 15}}

Next Step Evaluate

∴

a C,l = 5.50589652529656rad⁻¹

LAST Step Rounding Answer

∴

a C,l = 5.5059rad⁻¹

Lift Curve Slope for Finite Wing Formula Elements

Variables

Constants

Lift Curve Slope

The Lift Curve Slope is a measure of how rapidly the wing generates lift with a change in the angle of attack.

Symbol: a_C,l

Measurement: Reciprocal AngleUnit: rad⁻¹

Note: Value can be positive or negative.

Formulas to find Lift Curve Slope

2D Lift Curve Slope

The 2D Lift Curve Slope is a measure of how rapidly the airfoil generates lift with a change in angle of attack.

Symbol: a₀

Measurement: Reciprocal AngleUnit: rad⁻¹

Note: Value can be positive or negative.

Formulas to find 2D Lift Curve Slope

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.

Symbol: τ

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Induced Lift Slope Factor

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.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Wing Aspect Ratio

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

Other Formulas to find Lift Curve Slope

Go Lift Curve Slope for Elliptic Finite Wing

a C,l = \frac{a 0}{1 + \frac{a 0}{π \cdot AR}}

Other formulas in Flow over Wings category

Go Effective Angle of Attack of Finite Wing

α eff = α g - α i

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

a 0 = \frac{a C,l}{1 - \frac{a C,l \cdot (1 + τ)}{π \cdot AR}}

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

a 0 = \frac{a C,l}{1 - \frac{a C,l}{π \cdot AR}}

Go Aspect Ratio given Span Efficiency Factor

AR = \frac{{C L}^{2}}{π \cdot e span \cdot C D,i}

How to Evaluate Lift Curve Slope for Finite Wing?

Lift Curve Slope for Finite Wing evaluator uses Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)) to evaluate 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 evaluate Lift Curve Slope for Finite Wing using this online evaluator? To use this online evaluator 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.

FAQs on Lift Curve Slope for Finite Wing

What is the formula to find Lift Curve Slope for Finite Wing?

The formula of Lift Curve Slope for Finite Wing is expressed as Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). Here is an example- 5.505897 = 6.28/(1+(6.28*(1+0.055))/(pi*15)).

How to calculate Lift Curve Slope for Finite Wing?

With 2D Lift Curve Slope (a₀), Induced Lift Slope Factor (τ) & Wing Aspect Ratio (AR) we can find Lift Curve Slope for Finite Wing using the formula - Lift Curve Slope = 2D Lift Curve Slope/(1+(2D Lift Curve Slope*(1+Induced Lift Slope Factor))/(pi*Wing Aspect Ratio)). This formula also uses Archimedes' constant .

What are the other ways to Calculate Lift Curve Slope?

Here are the different ways to Calculate Lift Curve Slope-

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

Can the Lift Curve Slope for Finite Wing be negative?

Yes, the Lift Curve Slope for Finite Wing, measured in Reciprocal Angle can be negative.

Which unit is used to measure Lift Curve Slope for Finite Wing?

Lift Curve Slope for Finite Wing is usually measured using the 1 per Radian[rad⁻¹] for Reciprocal Angle. 1 per Degree[rad⁻¹], 1 per Minute[rad⁻¹], 1 per Quadrant[rad⁻¹] are the few other units in which Lift Curve Slope for Finite Wing can be measured.

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Lift Curve Slope for Finite Wing Formula

​GoLift Curve Slope for Elliptic Finite Wing Formula

Lift Curve Slope for Finite Wing Example

Lift Curve Slope for Finite Wing Solution

Lift Curve Slope for Finite Wing Formula Elements

Other Formulas to find Lift Curve Slope

Other formulas in Flow over Wings category

How to Evaluate Lift Curve Slope for Finite Wing?

FAQs on Lift Curve Slope for Finite Wing

Variable Name

GoLift Curve Slope for Elliptic Finite Wing Formula