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Induced Angle of Attack given Coefficient of Lift Formula

GoInduced Angle of Attack given Aspect Ratio Formula

GoInduced Angle of Attack given Circulation at Origin Formula

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The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity. Check FAQs

α i = S 0 \cdot \frac{C l}{π \cdot b^{2}}

α_i - Induced Angle of Attack?S₀ - Reference Area Origin?C_l - Lift Coefficient Origin?b - Wingspan?π - Archimedes' constant?

Induced Angle of Attack given Coefficient of Lift Example

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Here is how the Induced Angle of Attack given Coefficient of Lift equation looks like with Values.

Here is how the Induced Angle of Attack given Coefficient of Lift equation looks like with Units.

Here is how the Induced Angle of Attack given Coefficient of Lift equation looks like.

11.0414 = 2.21 \cdot \frac{1.5}{3.1416 \cdot 2340^{2}}

11.0414° = 2.21m² \cdot \frac{1.5}{3.1416 \cdot {2340mm}^{2}}

11.0414 = 2.21 \cdot \frac{1.5}{3.1416 \cdot 2340^{2}}

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Induced Angle of Attack given Coefficient of Lift Solution

Follow our step by step solution on how to calculate Induced Angle of Attack given Coefficient of Lift?

FIRST Step Consider the formula

α i = S 0 \cdot \frac{C l}{π \cdot b^{2}}

Next Step Substitute values of Variables

∴

α i = 2.21m² \cdot \frac{1.5}{π \cdot {2340mm}^{2}}

Next Step Substitute values of Constants

∴

α i = 2.21m² \cdot \frac{1.5}{3.1416 \cdot {2340mm}^{2}}

Next Step Convert Units

∴

α i = 2.21m² \cdot \frac{1.5}{3.1416 \cdot {2.34m}^{2}}

Next Step Prepare to Evaluate

∴

α i = 2.21 \cdot \frac{1.5}{3.1416 \cdot {2.34}^{2}}

Next Step Evaluate

∴

α i = 0.192708976678221rad

Next Step Convert to Output's Unit

∴

α i = 11.0414110379491°

LAST Step Rounding Answer

∴

α i = 11.0414°

Induced Angle of Attack given Coefficient of Lift Formula Elements

Variables

Constants

Induced Angle of Attack

The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

Symbol: α_i

Measurement: AngleUnit: °

Note: Value can be positive or negative.

Formulas to find Induced Angle of Attack

Reference Area Origin

Reference Area Origin is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area.

Symbol: S₀

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area Origin

Lift Coefficient Origin

Lift Coefficient Origin is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity, and an associated reference area.

Symbol: C_l

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient Origin

Wingspan

The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

Symbol: b

Measurement: LengthUnit: mm

Note: Value should be greater than 0.

Formulas to find Wingspan

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 Induced Angle of Attack

Go Induced Angle of Attack given Aspect Ratio

α i = \frac{C l}{π \cdot AR ELD}

Go Induced Angle of Attack given Circulation at Origin

α i = \frac{Γ o}{2 \cdot b \cdot V ∞}

Go Induced Angle of Attack given Downwash

α i = - (\frac{w}{V ∞})

Other formulas in Elliptical Lift Distribution category

Go Circulation at given Distance along Wingspan

Γ = Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Lift at given Distance along Wingspan

L = ρ ∞ \cdot V ∞ \cdot Γ o \cdot \sqrt{1 - {(2 \cdot \frac{a}{b})}^{2}}

Go Downwash in Elliptical Lift Distribution

w = - \frac{Γ o}{2 \cdot b}

Go Circulation at Origin in Elliptical Lift Distribution

Γ o = 2 \cdot V ∞ \cdot S 0 \cdot \frac{C l}{π \cdot b}

How to Evaluate Induced Angle of Attack given Coefficient of Lift?

Induced Angle of Attack given Coefficient of Lift evaluator uses Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2) to evaluate the Induced Angle of Attack, The Induced angle of attack given coefficient of lift formula calculates the angle between the direction of the freestream velocity and the local relative wind. Induced Angle of Attack is denoted by α_i symbol.

How to evaluate Induced Angle of Attack given Coefficient of Lift using this online evaluator? To use this online evaluator for Induced Angle of Attack given Coefficient of Lift, enter Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b) and hit the calculate button.

FAQs on Induced Angle of Attack given Coefficient of Lift

What is the formula to find Induced Angle of Attack given Coefficient of Lift?

The formula of Induced Angle of Attack given Coefficient of Lift is expressed as Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2). Here is an example- 632.6263 = 2.21*1.5/(pi*2.34^2).

How to calculate Induced Angle of Attack given Coefficient of Lift?

With Reference Area Origin (S₀), Lift Coefficient Origin (C_l) & Wingspan (b) we can find Induced Angle of Attack given Coefficient of Lift using the formula - Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2). This formula also uses Archimedes' constant .

What are the other ways to Calculate Induced Angle of Attack?

Here are the different ways to Calculate Induced Angle of Attack-

Induced Angle of Attack=Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)
Induced Angle of Attack=Circulation at Origin/(2*Wingspan*Freestream Velocity)
Induced Angle of Attack=-(Downwash/Freestream Velocity)

Can the Induced Angle of Attack given Coefficient of Lift be negative?

Yes, the Induced Angle of Attack given Coefficient of Lift, measured in Angle can be negative.

Which unit is used to measure Induced Angle of Attack given Coefficient of Lift?

Induced Angle of Attack given Coefficient of Lift is usually measured using the Degree[°] for Angle. Radian[°], Minute[°], Second[°] are the few other units in which Induced Angle of Attack given Coefficient of Lift can be measured.

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Induced Angle of Attack given Coefficient of Lift Formula

​GoInduced Angle of Attack given Aspect Ratio Formula

​GoInduced Angle of Attack given Circulation at Origin Formula

Induced Angle of Attack given Coefficient of Lift Example

Induced Angle of Attack given Coefficient of Lift Solution

Induced Angle of Attack given Coefficient of Lift Formula Elements

Other Formulas to find Induced Angle of Attack

Other formulas in Elliptical Lift Distribution category

How to Evaluate Induced Angle of Attack given Coefficient of Lift?

FAQs on Induced Angle of Attack given Coefficient of Lift

Variable Name

GoInduced Angle of Attack given Aspect Ratio Formula

GoInduced Angle of Attack given Circulation at Origin Formula