Effective Angle of Attack of Finite Wing Calculator

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

✖Effective Angle of Attack is the angle between the chord line and the direction of the local relative wind.ⓘ Effective Angle of Attack of Finite Wing [α_eff]

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Effective Angle of Attack of Finite Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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

Geometric Angle of Attack: 12 Degree --> 0.20943951023928 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_eff = α_g-α_i --> 0.20943951023928-0.0698131700797601

Evaluating ... ...

α_eff = 0.13962634015952

STEP 3: Convert Result to Output's Unit

0.13962634015952 Radian -->7.99999999999999 Degree (Check conversion here)

FINAL ANSWER

7.99999999999999 ≈ 8 Degree <-- Effective 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 » Aerospace » Flow over Wings » Effective Angle of Attack of Finite Wing

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Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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< Flow over Wings Calculators

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

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

Effective Angle of Attack of Finite Wing

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

Effective Angle of Attack of Finite Wing Formula

LaTeX Go

Effective Angle of Attack = Geometric Angle of Attack-Induced Angle of Attack
α_eff = α_g-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 Effective Angle of Attack of Finite Wing?

Effective Angle of Attack of Finite Wing calculator uses Effective Angle of Attack = Geometric Angle of Attack-Induced Angle of Attack to calculate the Effective Angle of Attack, The Effective Angle of Attack of Finite Wing formula calculates the angle between the chord line of the wing and the direction of the local relative wind. Effective Angle of Attack is denoted by α_eff symbol.

How to calculate Effective Angle of Attack of Finite Wing using this online calculator? To use this online calculator for Effective Angle of Attack of Finite Wing, enter Geometric Angle of Attack (α_g) & Induced Angle of Attack (α_i) and hit the calculate button. Here is how the Effective Angle of Attack of Finite Wing calculation can be explained with given input values -> 458.3662 = 0.20943951023928-0.0698131700797601.

FAQ

What is Effective Angle of Attack of Finite Wing?

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

How to calculate Effective Angle of Attack of Finite Wing?

The Effective Angle of Attack of Finite Wing formula calculates the angle between the chord line of the wing and the direction of the local relative wind is calculated using Effective Angle of Attack = Geometric Angle of Attack-Induced Angle of Attack. To calculate Effective Angle of Attack of Finite Wing, you need Geometric Angle of Attack (α_g) & Induced Angle of Attack (α_i). With our tool, you need to enter the respective value for Geometric 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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