Moment Produced by Vertical Tail for given Side Force Calculator

✖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 [Y_v]			+10% -10%

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment Produced by Vertical Tail for given Side Force [N_v]

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Formula

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Moment Produced by Vertical Tail for given Side Force

Formula

`"N"_{"v"} = -("𝒍"_{"v"}*"Y"_{"v"})`

Example

`"5.082N*m"=-("1.2m"*"-4.235N")`

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Moment Produced by Vertical Tail for given Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)
N_v = -(𝒍_v*Y_v)
This formula uses 3 Variables

Variables Used

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

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Side Force: -4.235 Newton --> -4.235 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

N_v = -(𝒍_v*Y_v) --> -(1.2*(-4.235))

Evaluating ... ...

N_v = 5.082

STEP 3: Convert Result to Output's Unit

5.082 Newton Meter --> No Conversion Required

FINAL ANSWER

5.082 Newton Meter <-- Vertical Tail Moment

(Calculation completed in 00.006 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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< 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 = Vertical Tail Moment/(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 = Vertical Tail Moment/(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 = Vertical Tail Moment/(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 Vertical Tail Moment = 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 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 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 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 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

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

Moment Produced by Vertical Tail for given Moment Coefficient

Go Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area

Vertical Tail Efficiency

Go Vertical Tail Efficiency = Vertical Tail Dynamic Pressure/Wing Dynamic Pressure

Moment Produced by Vertical Tail for given Side Force

Go Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)

Vertical Tail Side Force for Given Moment

Go Vertical Tail Side Force = -(Vertical Tail Moment/Vertical Tail Moment Arm)

Vertical Tail Moment Arm for given Side Force

Go Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force

Vertical Tail Angle of Attack

Go Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle

Moment Produced by Vertical Tail for given Side Force Formula

Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)
N_v = -(𝒍_v*Y_v)

What causes Dutch roll in aircraft?

Dutch roll is a natural aerodynamic phenomenon in swept-wing aircraft. It is caused by design having slightly weaker directional stability than lateral stability.

How to Calculate Moment Produced by Vertical Tail for given Side Force?

Moment Produced by Vertical Tail for given Side Force calculator uses Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force) to calculate the Vertical Tail Moment, Moment Produced by Vertical Tail for given Side Force is a measure of the rotating force that the vertical tail of an aircraft produces in response to a sideways force, calculated as the product of the vertical tail's moment arm and the side force, with the moment arm being the distance from the aircraft's axis of rotation to the vertical tail's centre of pressure, and the side force being the horizontal force acting on the vertical tail. Vertical Tail Moment is denoted by N_v symbol.

How to calculate Moment Produced by Vertical Tail for given Side Force using this online calculator? To use this online calculator for Moment Produced by Vertical Tail for given Side Force, enter Vertical Tail Moment Arm (𝒍_v) & Vertical Tail Side Force (Y_v) and hit the calculate button. Here is how the Moment Produced by Vertical Tail for given Side Force calculation can be explained with given input values -> 5.082 = -(1.2*(-4.235)).

FAQ

What is Moment Produced by Vertical Tail for given Side Force?

Moment Produced by Vertical Tail for given Side Force is a measure of the rotating force that the vertical tail of an aircraft produces in response to a sideways force, calculated as the product of the vertical tail's moment arm and the side force, with the moment arm being the distance from the aircraft's axis of rotation to the vertical tail's centre of pressure, and the side force being the horizontal force acting on the vertical tail and is represented as N_v = -(𝒍_v*Y_v) or Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force). 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 Side Force is the side force acting on the vertical tail of an aircraft.

How to calculate Moment Produced by Vertical Tail for given Side Force?

Moment Produced by Vertical Tail for given Side Force is a measure of the rotating force that the vertical tail of an aircraft produces in response to a sideways force, calculated as the product of the vertical tail's moment arm and the side force, with the moment arm being the distance from the aircraft's axis of rotation to the vertical tail's centre of pressure, and the side force being the horizontal force acting on the vertical tail is calculated using Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force). To calculate Moment Produced by Vertical Tail for given Side Force, you need Vertical Tail Moment Arm (𝒍_v) & Vertical Tail Side Force (Y_v). With our tool, you need to enter the respective value for Vertical Tail Moment Arm & Vertical Tail Side Force 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 Moment?

In this formula, Vertical Tail Moment uses Vertical Tail Moment Arm & Vertical Tail Side Force. We can use 2 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area
Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area

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