Angle of Attack at Tail Calculator

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Static Stability and 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%
✖Wing incidence angle is the angle between the chord of wing and fuselage reference line.ⓘ 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 Horizontal tail angle of attack is the angle of attack of the horizontal tail of an aircraft.ⓘ Angle of Attack at Tail [α_t]

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Formula

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Angle of Attack at Tail

Formula

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

Example

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

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Angle of Attack at Tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
Wing angle of attack - (Measured in Radian) - Wing angle of attack is the angle of attack of the wing of an aircraft.
Wing incidence angle - (Measured in Radian) - Wing incidence angle is the angle between the chord of wing and fuselage reference line.
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
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_t = α_w-𝒊_w-ε+𝒊_t --> 0.083-0.078-0.095+0.86

Evaluating ... ...

α_t = 0.77

STEP 3: Convert Result to Output's Unit

0.77 Radian --> No Conversion Required

FINAL ANSWER

0.77 Radian <-- Horizontal tail angle of attack

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

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

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Indian Institute of Technology (IIT), Bombay

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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 Attack at Tail Formula

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

What is the best angle of attack?

The best angle of attack is the angle that gives the best lift/drag (L/D) value and, thus, the highest cruise efficiency.

How to Calculate Angle of Attack at Tail?

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

How to calculate Angle of Attack at Tail using this online calculator? To use this online calculator for Angle of Attack at Tail, enter Wing angle of attack (α_w), 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 at Tail calculation can be explained with given input values -> 0.777 = 0.083-0.078-0.095+0.86.

FAQ

What is Angle of Attack at Tail?

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

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