Angle of Attack of Wing Calculator

✖The Horizontal Tail Angle of Attack (AoA) refers to the angle between the chord line of the horizontal stabilizer (including the elevator) and the relative airflow.ⓘ Horizontal Tail Angle of Attack [α_t]			+10% -10%
✖The Wing Incidence Angle refers to the angle between the chord line of the wing and the longitudinal axis (or fuselage reference line) of the aircraft.ⓘ Wing Incidence Angle [𝒊_w]			+10% -10%
✖Downwash Angle is the angle formed between the direction of air movement as it approaches an airfoil and as it leaves it.ⓘ Downwash Angle [ε]			+10% -10%
✖Tail Incidence Angle is the angle between the reference chord of the horizontal tail and the fuselage reference line.ⓘ Tail Incidence Angle [𝒊_t]			+10% -10%

✖The Wing Angle of Attack (AoA) refers to the angle between the chord line of the wing and the direction of the relative airflow.ⓘ Angle of Attack of Wing [α_w]

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Formula

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Angle of Attack of Wing

Formula

`"α"_{"w"} = "α"_{"t"}+"𝒊"_{"w"}+"ε"-"𝒊"_{"t"}`

Example

`"0.083rad"="0.77rad"+"0.078rad"+"0.095rad"-"0.86rad"`

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Angle of Attack of Wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle
α_w = α_t+𝒊_w+ε-𝒊_t
This formula uses 5 Variables

Variables Used

Wing Angle of Attack - (Measured in Radian) - The Wing Angle of Attack (AoA) refers to the angle between the chord line of the wing and the direction of the relative airflow.
Horizontal Tail Angle of Attack - (Measured in Radian) - The Horizontal Tail Angle of Attack (AoA) refers to the angle between the chord line of the horizontal stabilizer (including the elevator) and the relative airflow.
Wing Incidence Angle - (Measured in Radian) - The Wing Incidence Angle refers to the angle between the chord line of the wing and the longitudinal axis (or fuselage reference line) of the aircraft.
Downwash Angle - (Measured in Radian) - Downwash Angle is the angle formed between the direction of air movement as it approaches an airfoil and as it leaves it.
Tail Incidence Angle - (Measured in Radian) - Tail Incidence Angle is the angle between the reference chord of the horizontal tail and the fuselage reference line.

STEP 1: Convert Input(s) to Base Unit

Horizontal Tail Angle of Attack: 0.77 Radian --> 0.77 Radian No Conversion Required
Wing Incidence Angle: 0.078 Radian --> 0.078 Radian No Conversion Required
Downwash Angle: 0.095 Radian --> 0.095 Radian No Conversion Required
Tail Incidence Angle: 0.86 Radian --> 0.86 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_w = α_t+𝒊_w+ε-𝒊_t --> 0.77+0.078+0.095-0.86

Evaluating ... ...

α_w = 0.083

STEP 3: Convert Result to Output's Unit

0.083 Radian --> No Conversion Required

FINAL ANSWER

0.083 Radian <-- Wing Angle of Attack

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

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< 15 Wing-Tail Contribution Calculators

Tail Lift Coefficient for given Pitching Moment Coefficient

Go Tail Lift Coefficient = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord/(Tail Efficiency*Horizontal Tail Area*Horizontal Tail Moment Arm))

Tail Lift Coefficient for given Pitching Moment

Go Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^2*Horizontal Tail Area)

Tail Lift Coefficient of Wing-Tail Combination

Go Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal Tail Area)

Tail Efficiency for given lift coefficients

Go Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal Tail Area)

Tail area for given tail efficiency

Go Horizontal Tail Area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)

Total Lift Coefficient of Wing-Tail Combination

Go Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area)

Wing Lift Coefficient of wing-tail combination

Go Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area)

Angle of incidence of wing

Go Wing Incidence Angle = Wing Angle of Attack-Horizontal Tail Angle of Attack-Downwash Angle+Tail Incidence Angle

Angle of incidence of tail

Go Tail Incidence Angle = Horizontal Tail Angle of Attack-Wing Angle of Attack+Wing Incidence Angle+Downwash Angle

Angle of Attack at Tail

Go Horizontal Tail Angle of Attack = Wing Angle of Attack-Wing Incidence Angle-Downwash Angle+Tail Incidence Angle

Angle of Attack of Wing

Go Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle

Downwash angle

Go Downwash Angle = Wing Angle of Attack-Wing Incidence Angle-Horizontal Tail Angle of Attack+Tail Incidence Angle

Total Lift of Wing-Tail Combination

Go Lift Force = Lift due to Wing+Lift due to Tail

Lift due to Wing only

Go Lift due to Wing = Lift Force-Lift due to Tail

Lift due to Tail only

Go Lift due to Tail = Lift Force-Lift due to Wing

Angle of Attack of Wing Formula

Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle
α_w = α_t+𝒊_w+ε-𝒊_t

What is the stalling angle of attack?

A stall occurs when the angle of attack of an aerofoil exceeds the value, which creates maximum lift due to airflow across it. This angle varies very little in response to the cross-section of the (clean) aerofoil and is typically around 15°.

How to Calculate Angle of Attack of Wing?

Angle of Attack of Wing calculator uses Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle to calculate the Wing Angle of Attack, Angle of Attack of Wing is a measure of the angle between the wing and the oncoming airflow, calculated by adding the horizontal tail angle of attack, wing incidence angle, and downwash angle, and then subtracting the tail incidence angle, which is crucial in aerodynamics to determine the wing's performance and stability. Wing Angle of Attack is denoted by α_w symbol.

How to calculate Angle of Attack of Wing using this online calculator? To use this online calculator for Angle of Attack of Wing, enter Horizontal Tail Angle of Attack (α_t), Wing Incidence Angle (𝒊_w), Downwash Angle (ε) & Tail Incidence Angle (𝒊_t) and hit the calculate button. Here is how the Angle of Attack of Wing calculation can be explained with given input values -> 0.083 = 0.77+0.078+0.095-0.86.

FAQ

What is Angle of Attack of Wing?

Angle of Attack of Wing is a measure of the angle between the wing and the oncoming airflow, calculated by adding the horizontal tail angle of attack, wing incidence angle, and downwash angle, and then subtracting the tail incidence angle, which is crucial in aerodynamics to determine the wing's performance and stability and is represented as α_w = α_t+𝒊_w+ε-𝒊_t or Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle. The Horizontal Tail Angle of Attack (AoA) refers to the angle between the chord line of the horizontal stabilizer (including the elevator) and the relative airflow, The Wing Incidence Angle refers to the angle between the chord line of the wing and the longitudinal axis (or fuselage reference line) of the aircraft, Downwash Angle is the angle formed between the direction of air movement as it approaches an airfoil and as it leaves it & Tail Incidence Angle is the angle between the reference chord of the horizontal tail and the fuselage reference line.

How to calculate Angle of Attack of Wing?

Angle of Attack of Wing is a measure of the angle between the wing and the oncoming airflow, calculated by adding the horizontal tail angle of attack, wing incidence angle, and downwash angle, and then subtracting the tail incidence angle, which is crucial in aerodynamics to determine the wing's performance and stability is calculated using Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle. To calculate Angle of Attack of Wing, you need Horizontal Tail Angle of Attack (α_t), Wing Incidence Angle (𝒊_w), Downwash Angle (ε) & Tail Incidence Angle (𝒊_t). With our tool, you need to enter the respective value for Horizontal Tail Angle of Attack, Wing Incidence Angle, Downwash Angle & Tail Incidence Angle 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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