Angle of incidence of wing Calculator

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Static Stability and Control

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Introduction and Governing Equations

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Longitudinal Stability

Directional Control

Directional Stability

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Lateral Stability

Longitudinal Control

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Wing-Tail Contribution

Fuselage Contribution

Tail Contribution

✖Wing angle of attack is the angle of attack of the wing of an aircraft.ⓘ Wing angle of attack [α_w]			+10% -10%
✖The Horizontal tail angle of attack is the angle of attack of the horizontal tail of an aircraft.ⓘ Horizontal tail angle of attack [α_t]			+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%

✖Wing incidence angle is the angle between the chord of wing and fuselage reference line.ⓘ Angle of incidence of wing [𝒊_w]

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Formula

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Angle of incidence of wing

Formula

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

Example

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

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Angle of incidence of wing Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle
𝒊_w = α_w-α_t-ε+𝒊_t
This formula uses 5 Variables

Variables Used

Wing incidence angle - (Measured in Radian) - Wing incidence angle is the angle between the chord of wing and fuselage reference line.
Wing angle of attack - (Measured in Radian) - Wing angle of attack is the angle of attack of the wing of an aircraft.
Horizontal tail angle of attack - (Measured in Radian) - The Horizontal tail angle of attack is the angle of attack of the horizontal tail of an 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

Wing angle of attack: 0.083 Radian --> 0.083 Radian No Conversion Required
Horizontal tail angle of attack: 0.77 Radian --> 0.77 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

𝒊_w = α_w-α_t-ε+𝒊_t --> 0.083-0.77-0.095+0.86

Evaluating ... ...

𝒊_w = 0.078

STEP 3: Convert Result to Output's Unit

0.078 Radian --> No Conversion Required

FINAL ANSWER

0.078 Radian <-- Wing incidence angle

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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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*Tail Velocity^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 incidence of wing Formula

Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle
𝒊_w = α_w-α_t-ε+𝒊_t

Why is angle of incidence important?

The angle of incidence defines your angle of attack until you have enough speed (and tail downforce) to lift your nose off. And, the angle of incidence reduces your pitch angle, giving you better visibility during takeoff.

How to Calculate Angle of incidence of wing?

Angle of incidence of wing calculator uses Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle to calculate the Wing incidence angle, The Angle of incidence of wing is the sum of wing angle of attack and tail incidence angle minus the sum of tail angle of attack and downwash angle. . Wing incidence angle is denoted by 𝒊_w symbol.

How to calculate Angle of incidence of wing using this online calculator? To use this online calculator for Angle of incidence of wing, enter Wing angle of attack (α_w), Horizontal tail angle of attack (α_t), Downwash angle (ε) & Tail incidence angle (𝒊_t) and hit the calculate button. Here is how the Angle of incidence of wing calculation can be explained with given input values -> 0.085 = 0.083-0.77-0.095+0.86.

FAQ

What is Angle of incidence of wing?

The Angle of incidence of wing is the sum of wing angle of attack and tail incidence angle minus the sum of tail angle of attack and downwash angle. and is represented as 𝒊_w = α_w-α_t-ε+𝒊_t or Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle. Wing angle of attack is the angle of attack of the wing of an aircraft, The Horizontal tail angle of attack is the angle of attack of the horizontal tail of an 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 incidence of wing?

The Angle of incidence of wing is the sum of wing angle of attack and tail incidence angle minus the sum of tail angle of attack and downwash angle. is calculated using Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle. To calculate Angle of incidence of wing, you need Wing angle of attack (α_w), Horizontal tail angle of attack (α_t), Downwash angle (ε) & Tail incidence angle (𝒊_t). With our tool, you need to enter the respective value for Wing angle of attack, Horizontal tail angle of attack, 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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