Induced Angle of Attack given Circulation at Origin Calculator

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Two-Dimensional Incompressible Flow

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Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Lift Distribution

Elementary Flows

Flow and Lift Distribution

Flow over Airfoils and Wings

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Elliptical Lift Distribution

General Lift Distribution

✖Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.ⓘ Circulation at Origin [Γ_o]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.ⓘ Freestream Velocity [V_∞]			+10% -10%

✖The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.ⓘ Induced Angle of Attack given Circulation at Origin [α_i]

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Formula

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Induced Angle of Attack given Circulation at Origin

Formula

`"α"_{"i"} = "Γ"_{"o"}/(2*"b"*"V"_{"∞"})`

Example

`"11.05791°"="14m²/s"/(2*"2340mm"*"15.5m/s")`

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Induced Angle of Attack given Circulation at Origin Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)
α_i = Γ_o/(2*b*V_∞)
This formula uses 4 Variables

Variables Used

Induced Angle of Attack - (Measured in Radian) - The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.
Circulation at Origin - (Measured in Square Meter per Second) - Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.

STEP 1: Convert Input(s) to Base Unit

Circulation at Origin: 14 Square Meter per Second --> 14 Square Meter per Second No Conversion Required
Wingspan: 2340 Millimeter --> 2.34 Meter (Check conversion here)
Freestream Velocity: 15.5 Meter per Second --> 15.5 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_i = Γ_o/(2*b*V_∞) --> 14/(2*2.34*15.5)

Evaluating ... ...

α_i = 0.192996967190516

STEP 3: Convert Result to Output's Unit

0.192996967190516 Radian -->11.0579116788434 Degree (Check conversion here)

FINAL ANSWER

11.0579116788434 ≈ 11.05791 Degree <-- Induced Angle of Attack

(Calculation completed in 00.004 seconds)

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< 20 Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

Go Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Circulation at Origin in Elliptical Lift Distribution

Go Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)

Coefficient of Lift given Circulation at Origin

Go Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin)

Freestream Velocity given Circulation at Origin

Go Freestream Velocity = pi*Wingspan*Circulation at Origin/(2*Reference Area Origin*Lift Coefficient ELD)

Lift of Wing given Circulation at Origin

Go Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4

Circulation at Origin given Lift of Wing

Go Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)

Induced Angle of Attack given Coefficient of Lift

Go Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)

Circulation at given Distance along Wingspan

Go Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Coefficient of Lift given Induced Drag Coefficient

Go Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)

Aspect Ratio given Induced Drag Coefficient

Go Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)

Induced Drag Coefficient given Aspect Ratio

Go Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)

Induced Angle of Attack given Circulation at Origin

Go Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)

Freestream Velocity given Induced Angle of Attack

Go Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)

Circulation at Origin given Induced Angle of Attack

Go Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity

Induced Angle of Attack given Aspect Ratio

Go Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)

Aspect Ratio given Induced Angle of Attack

Go Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack)

Coefficient of Lift given Induced Angle of Attack

Go Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD

Induced Angle of Attack given Downwash

Go Induced Angle of Attack = -(Downwash/Freestream Velocity)

Downwash in Elliptical Lift Distribution

Go Downwash = -Circulation at Origin/(2*Wingspan)

Circulation at Origin given Downwash

Go Circulation at Origin = -2*Downwash*Wingspan

Induced Angle of Attack given Circulation at Origin Formula

Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)
α_i = Γ_o/(2*b*V_∞)

How does angle of attack affect the airfoil?

An increase in the angle of attack results in an increase in both lift and induced drag, up to a point. Too high an angle of attack (usually around 17 degrees) and the airflow across the upper surface of the aerofoil become detached, resulting in a loss of lift, otherwise known as a Stall.

How to Calculate Induced Angle of Attack given Circulation at Origin?

Induced Angle of Attack given Circulation at Origin calculator uses Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity) to calculate the Induced Angle of Attack, The Induced Angle of Attack given Circulation at Origin formula calculates the angle between the local relative wind and the direction of freestream velocity called the induced angle of attack by using the circulation at the origin. Induced Angle of Attack is denoted by α_i symbol.

How to calculate Induced Angle of Attack given Circulation at Origin using this online calculator? To use this online calculator for Induced Angle of Attack given Circulation at Origin, enter Circulation at Origin (Γ_o), Wingspan (b) & Freestream Velocity (V_∞) and hit the calculate button. Here is how the Induced Angle of Attack given Circulation at Origin calculation can be explained with given input values -> 633.5717 = 14/(2*2.34*15.5).

FAQ

What is Induced Angle of Attack given Circulation at Origin?

The Induced Angle of Attack given Circulation at Origin formula calculates the angle between the local relative wind and the direction of freestream velocity called the induced angle of attack by using the circulation at the origin and is represented as α_i = Γ_o/(2*b*V_∞) or Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity). Circulation at Origin is the circulation when the origin is taken at the center of the bound vortex, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.

How to calculate Induced Angle of Attack given Circulation at Origin?

The Induced Angle of Attack given Circulation at Origin formula calculates the angle between the local relative wind and the direction of freestream velocity called the induced angle of attack by using the circulation at the origin is calculated using Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity). To calculate Induced Angle of Attack given Circulation at Origin, you need Circulation at Origin (Γ_o), Wingspan (b) & Freestream Velocity (V_∞). With our tool, you need to enter the respective value for Circulation at Origin, Wingspan & Freestream Velocity 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 Induced Angle of Attack?

In this formula, Induced Angle of Attack uses Circulation at Origin, Wingspan & Freestream Velocity. We can use 3 other way(s) to calculate the same, which is/are as follows -

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

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