Geometric Angle of Attack given Effective Angle of Attack Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Flow over Airfoils and Wings

Elementary Flows

Flow and Lift Distribution

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✖Effective Angle of Attack is the angle between the chord line and the direction of the local relative wind.ⓘ Effective Angle of Attack [α_eff]			+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 [α_i]			+10% -10%

✖The Geometric Angle of Attack is the angle between the direction of freestream velocity and the chord line.ⓘ Geometric Angle of Attack given Effective Angle of Attack [α_g]

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Formula

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Geometric Angle of Attack given Effective Angle of Attack

Formula

`"α"_{"g"} = "α"_{"eff"}+"α"_{"i"}`

Example

`"12°"="8°"+"4°"`

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Geometric Angle of Attack given Effective Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack
α_g = α_eff+α_i
This formula uses 3 Variables

Variables Used

Geometric Angle of Attack - (Measured in Radian) - The Geometric Angle of Attack is the angle between the direction of freestream velocity and the chord line.
Effective Angle of Attack - (Measured in Radian) - Effective Angle of Attack is the angle between the chord line and the direction of the local relative wind.
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.

STEP 1: Convert Input(s) to Base Unit

Effective Angle of Attack: 8 Degree --> 0.13962634015952 Radian (Check conversion here)
Induced Angle of Attack: 4 Degree --> 0.0698131700797601 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_g = α_eff+α_i --> 0.13962634015952+0.0698131700797601

Evaluating ... ...

α_g = 0.20943951023928

STEP 3: Convert Result to Output's Unit

0.20943951023928 Radian -->12 Degree (Check conversion here)

FINAL ANSWER

12 Degree <-- Geometric Angle of Attack

(Calculation completed in 00.004 seconds)

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Home » Physics » Aerodynamics » Two-Dimensional Incompressible Flow » Flow over Airfoils and Wings » Flow over Wings » Geometric Angle of Attack given Effective Angle of Attack

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< 11 Flow over Wings Calculators

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

Lift Curve Slope for Finite Wing

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

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

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

Aspect Ratio given Span Efficiency Factor

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

Aspect Ratio of Wing given Lift Curve Slope of Elliptic Finite Wing

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

Lift Curve Slope for Elliptic Finite Wing

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

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

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

Geometric Angle of Attack given Effective Angle of Attack

Go Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack

Induced Angle of Attack given Effective Angle of Attack

Go Induced Angle of Attack = Geometric Angle of Attack-Effective Angle of Attack

Effective Angle of Attack of Finite Wing

Go Effective Angle of Attack = Geometric Angle of Attack-Induced Angle of Attack

Oswald Efficiency Factor

Go Oswald Efficiency Factor = 1.78*(1-0.045*Wing Aspect Ratio^(0.68))-0.64

Geometric Angle of Attack given Effective Angle of Attack Formula

Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack
α_g = α_eff+α_i

What is the effect of angle of attack?

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 Geometric Angle of Attack given Effective Angle of Attack?

Geometric Angle of Attack given Effective Angle of Attack calculator uses Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack to calculate the Geometric Angle of Attack, The Geometric Angle of Attack given Effective Angle of Attack formula calculates the angle between the chord line of the wing and the direction of the freestream velocity. Geometric Angle of Attack is denoted by α_g symbol.

How to calculate Geometric Angle of Attack given Effective Angle of Attack using this online calculator? To use this online calculator for Geometric Angle of Attack given Effective Angle of Attack, enter Effective Angle of Attack (α_eff) & Induced Angle of Attack (α_i) and hit the calculate button. Here is how the Geometric Angle of Attack given Effective Angle of Attack calculation can be explained with given input values -> 1088.62 = 0.13962634015952+0.0698131700797601.

FAQ

What is Geometric Angle of Attack given Effective Angle of Attack?

The Geometric Angle of Attack given Effective Angle of Attack formula calculates the angle between the chord line of the wing and the direction of the freestream velocity and is represented as α_g = α_eff+α_i or Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack. Effective Angle of Attack is the angle between the chord line and the direction of the local relative wind & The Induced Angle of Attack is the angle between the local relative wind and the direction of freestream velocity.

How to calculate Geometric Angle of Attack given Effective Angle of Attack?

The Geometric Angle of Attack given Effective Angle of Attack formula calculates the angle between the chord line of the wing and the direction of the freestream velocity is calculated using Geometric Angle of Attack = Effective Angle of Attack+Induced Angle of Attack. To calculate Geometric Angle of Attack given Effective Angle of Attack, you need Effective Angle of Attack (α_eff) & Induced Angle of Attack (α_i). With our tool, you need to enter the respective value for Effective Angle of Attack & Induced Angle of Attack 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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