Vertical tail side force for given moment 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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Vertical Tail Contribution

Aerodynamic Parameters

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%

✖Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.ⓘ Vertical tail side force for given moment [Y_v]

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Formula

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Vertical tail side force for given moment

Formula

`"Y"_{"v"} = "N"_{"v"}/"𝒍"_{"v"}`

Example

`"1.666667N"="2N*m"/"1.2m"`

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Vertical tail side force for given moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm
Y_v = N_v/𝒍_v
This formula uses 3 Variables

Variables Used

Vertical Tail Side Force - (Measured in Newton) - Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.
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.

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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Y_v = N_v/𝒍_v --> 2/1.2

Evaluating ... ...

Y_v = 1.66666666666667

STEP 3: Convert Result to Output's Unit

1.66666666666667 Newton --> No Conversion Required

FINAL ANSWER

1.66666666666667 ≈ 1.666667 Newton <-- Vertical Tail Side Force

(Calculation completed in 00.004 seconds)

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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!

Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 200+ more calculators!

< 24 Vertical Tail Contribution Calculators

Vertical tail moment arm for given yawing moment coefficient

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

Vertical tail area for given yawing moment coefficient

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

Vertical tail lift curve slope for given yawing moment coefficient

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

Vertical tail moment arm for given lift curve slope

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

Vertical tail lift curve slope for given moment

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

Vertical tail area for given moment

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

Moment produced by vertical tail for given lift curve slope

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

Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency

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

Vertical tail volume ratio for given yawing moment coefficient

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

Vertical tail efficiency for given yawing moment coefficient

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

Vertical tail area for given vertical tail side force

Go Vertical tail area = -(Vertical Tail Side Force)/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail dynamic pressure)

Vertical tail dynamic pressure for given vertical tail side force

Go Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area)

Vertical tail angle of attack for given vertical tail side force

Go Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail lift curve slope

Go Vertical tail Lift curve slope = -Vertical Tail Side Force/(Vertical tail angle of attack*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail Side force

Go Vertical Tail Side Force = -Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure

Moment produced by vertical tail for given moment coefficient

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

Vertical tail volume ratio

Go Vertical Tail Volume Ratio = Vertical tail moment arm*Vertical tail area/(Reference Area*Wingspan)

Vertical tail moment arm for given vertical tail volume ratio

Go Vertical tail moment arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail area

Vertical tail area for given vertical tail volume ratio

Go Vertical tail area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail moment arm

Vertical tail moment arm for given side force

Go Vertical tail moment arm = -Moment produced by vertical tail/Vertical Tail Side Force

Moment produced by vertical tail for given side force

Go Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force

Vertical tail side force for given moment

Go Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm

Vertical tail efficiency

Go Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure

Vertical tail angle of attack

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

Vertical tail side force for given moment Formula

Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm
Y_v = N_v/𝒍_v

What is keel effect on a plane?

In aeronautics, the keel effect (also known as the pendulum effect or pendulum stability) is the result of the side force-generating surfaces being above (or below) the center of mass (which coincides with the center of gravity) in an aircraft.

How to Calculate Vertical tail side force for given moment?

Vertical tail side force for given moment calculator uses Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm to calculate the Vertical Tail Side Force, The Vertical tail side force for given moment is the ratio of the moment produced by the vertical tail and its moment arm. Vertical Tail Side Force is denoted by Y_v symbol.

How to calculate Vertical tail side force for given moment using this online calculator? To use this online calculator for Vertical tail side force for given moment, enter Moment produced by vertical tail (N_v) & Vertical tail moment arm (𝒍_v) and hit the calculate button. Here is how the Vertical tail side force for given moment calculation can be explained with given input values -> 1.666667 = 2/1.2.

FAQ

What is Vertical tail side force for given moment?

The Vertical tail side force for given moment is the ratio of the moment produced by the vertical tail and its moment arm and is represented as Y_v = N_v/𝒍_v or Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm. 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.

How to calculate Vertical tail side force for given moment?

The Vertical tail side force for given moment is the ratio of the moment produced by the vertical tail and its moment arm is calculated using Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm. To calculate Vertical tail side force for given moment, you need Moment produced by vertical tail (N_v) & Vertical tail moment arm (𝒍_v). With our tool, you need to enter the respective value for Moment produced by vertical tail & Vertical tail moment arm 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 Vertical Tail Side Force?

In this formula, Vertical Tail Side Force uses Moment produced by vertical tail & Vertical tail moment arm. We can use 1 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Side Force = -Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure

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