Downwash angle 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%
✖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%
✖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%

✖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]

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Formula

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Downwash angle

Formula

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

Example

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

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Downwash angle Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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.
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
Horizontal tail angle of attack: 0.77 Radian --> 0.77 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

ε = α_w-𝒊_w-α_t+𝒊_t --> 0.083-0.078-0.77+0.86

Evaluating ... ...

ε = 0.095

STEP 3: Convert Result to Output's Unit

0.095 Radian --> No Conversion Required

FINAL ANSWER

0.095 Radian <-- Downwash angle

(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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Verified by Shikha Maurya

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

Downwash angle Formula

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

What causes downwash?

The more air that a wing diverts down, the more lift it can produce. A huge column of air moves almost straight down relative to the ground. This is the downwash created by the wings of the jet resulting in an opposing lift force.

How to Calculate Downwash angle?

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

How to calculate Downwash angle using this online calculator? To use this online calculator for Downwash angle, enter Wing angle of attack (α_w), Wing incidence angle (𝒊_w), Horizontal tail angle of attack (α_t) & Tail incidence angle (𝒊_t) and hit the calculate button. Here is how the Downwash angle calculation can be explained with given input values -> 0.102 = 0.083-0.078-0.77+0.86.

FAQ

What is Downwash angle?

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

How to calculate Downwash angle?

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