Sidewash angle for given moment produced by vertical tail Calculator

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Static Stability and Control

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

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Directional Stability

Longitudinal Stability

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Aerodynamic Parameters

Vertical Tail Contribution

Wing-Tail Interaction

✖The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment produced by vertical tail [N_v]			+10% -10%
✖The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical tail moment arm [𝒍_v]			+10% -10%
✖The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical tail Lift curve slope [C_v]			+10% -10%
✖Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical tail dynamic pressure [Q_v]			+10% -10%
✖The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical tail area [S_v]			+10% -10%
✖The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.ⓘ Sideslip angle [β]			+10% -10%

✖Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.ⓘ Sidewash angle for given moment produced by vertical tail [σ]

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Formula

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Sidewash angle for given moment produced by vertical tail

Formula

`"σ" = ("N"_{"v"}/("𝒍"_{"v"}*"C"_{"v"}*"Q"_{"v"}*"S"_{"v"}))-"β"`

Example

`"-0.00671rad"=("2N*m"/("1.2m"*"0.7rad⁻¹"*"11Pa"*"5m²"))-"0.05rad"`

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Sidewash angle for given moment produced by vertical tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle
σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β
This formula uses 7 Variables

Variables Used

Sidewash angle - (Measured in Radian) - Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Vertical tail moment arm - (Measured in Meter) - The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical tail Lift curve slope - (Measured in 1 per Radian) - The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Vertical tail dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Vertical tail area - (Measured in Square Meter) - The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Sideslip angle - (Measured in Radian) - The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.

STEP 1: Convert Input(s) to Base Unit

Moment produced by vertical tail: 2 Newton Meter --> 2 Newton Meter No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required
Sideslip angle: 0.05 Radian --> 0.05 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β --> (2/(1.2*0.7*11*5))-0.05

Evaluating ... ...

σ = -0.00670995670995671

STEP 3: Convert Result to Output's Unit

-0.00670995670995671 Radian --> No Conversion Required

FINAL ANSWER

-0.00670995670995671 ≈ -0.00671 Radian <-- Sidewash angle

(Calculation completed in 00.022 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 Anshika Arya

National Institute Of Technology (NIT), Hamirpur

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< 10+ Aerodynamic Parameters Calculators

Yawing moment coefficient for given vertical tail lift curve slope

Go Yawing moment coefficient = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure)

Sidewash Angle given Yawing Moment Coefficient using Wingspan

Go Sidewash angle = (Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope))-Sideslip angle

Sideslip angle for given moment produced by vertical tail

Go Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle

Sidewash angle for given moment produced by vertical tail

Go Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle

Sideslip angle for yawing moment coefficient given vertical tail volume ratio

Go Sideslip angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sidewash angle

Sidewash angle for given yawing moment coefficient

Go Sidewash angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle

Yawing moment coefficient for given vertical tail volume ratio

Go Yawing moment coefficient = Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)

Yawing Moment Coefficient using Wingspan

Go Yawing moment coefficient = Moment produced by vertical tail/(Wing dynamic pressure*Reference Area*Wingspan)

Sideslip angle for Aircraft

Go Sideslip angle = Vertical tail angle of attack-Sidewash angle

Sidewash angle

Go Sidewash angle = Vertical tail angle of attack-Sideslip angle

Sidewash angle for given moment produced by vertical tail Formula

Why do airplanes Bank when they turn?

Airplanes bank when they turn because, in order to turn, there must be a force that will be exerted towards the center of a circle. By tilting the wings, the lift force on the wings has a non-vertical component that points toward the center of the curve, providing the centripetal force.

How to Calculate Sidewash angle for given moment produced by vertical tail?

Sidewash angle for given moment produced by vertical tail calculator uses Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle to calculate the Sidewash angle, The Sidewash angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sideslip angle. Sidewash angle is denoted by σ symbol.

How to calculate Sidewash angle for given moment produced by vertical tail using this online calculator? To use this online calculator for Sidewash angle for given moment produced by vertical tail, enter Moment produced by vertical tail (N_v), Vertical tail moment arm (𝒍_v), Vertical tail Lift curve slope (C_v), Vertical tail dynamic pressure (Q_v), Vertical tail area (S_v) & Sideslip angle (β) and hit the calculate button. Here is how the Sidewash angle for given moment produced by vertical tail calculation can be explained with given input values -> -0.00671 = (2/(1.2*0.7*11*5))-0.05.

FAQ

What is Sidewash angle for given moment produced by vertical tail?

The Sidewash angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sideslip angle and is represented as σ = (N_v/(𝒍_v*C_v*Q_v*S_v))-β or Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle. The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline & The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.

How to calculate Sidewash angle for given moment produced by vertical tail?

The Sidewash angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sideslip angle is calculated using Sidewash angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sideslip angle. To calculate Sidewash angle for given moment produced by vertical tail, you need Moment produced by vertical tail (N_v), Vertical tail moment arm (𝒍_v), Vertical tail Lift curve slope (C_v), Vertical tail dynamic pressure (Q_v), Vertical tail area (S_v) & Sideslip angle (β). With our tool, you need to enter the respective value for Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Vertical tail dynamic pressure, Vertical tail area & Sideslip angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Sidewash angle?

In this formula, Sidewash angle uses Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Vertical tail dynamic pressure, Vertical tail area & Sideslip angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Sidewash angle = Vertical tail angle of attack-Sideslip angle
Sidewash angle = (Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope))-Sideslip angle
Sidewash angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sideslip angle

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