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
αw = αt+𝒊w+ε-𝒊t
This formula uses 5 Variables
Variables Used
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.
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
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
αw = αt+𝒊w+ε-𝒊t --> 0.77+0.078+0.095-0.86
Evaluating ... ...
αw = 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)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ more calculators!

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 of wing Formula

Wing angle of attack = Horizontal tail angle of attack+Wing incidence angle+Downwash angle-Tail incidence angle
αw = αt+𝒊w+ε-𝒊t

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, The Angle of attack of wing is the sum of the tail angle of attack, wing incidence angle, downwash angle minus the tail incidence angle. Wing angle of attack is denoted by αw 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 t), Wing incidence angle (𝒊w), Downwash angle (ε) & Tail incidence angle (𝒊t) 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?
The Angle of attack of wing is the sum of the tail angle of attack, wing incidence angle, downwash angle minus the tail incidence angle and is represented as αw = αt+𝒊w+ε-𝒊t or Wing angle of attack = Horizontal tail angle of attack+Wing incidence angle+Downwash angle-Tail incidence angle. The Horizontal tail angle of attack is the angle of attack of the horizontal tail 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 of wing?
The Angle of attack of wing is the sum of the tail angle of attack, wing incidence angle, downwash angle minus the tail incidence angle 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 t), Wing incidence angle (𝒊w), Downwash angle (ε) & Tail incidence angle (𝒊t). 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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