Vertical Tail Side Force for Given Moment Calculator

✖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 [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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Vertical Tail Side Force for Given Moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Side Force = -(Vertical Tail Moment/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.
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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 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) --> -(5.4/1.2)

Evaluating ... ...

Y_v = -4.5

STEP 3: Convert Result to Output's Unit

-4.5 Newton --> No Conversion Required

FINAL ANSWER

-4.5 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

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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX 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

LaTeX 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

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

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

Vertical Tail Side Force for Given Moment Formula

LaTeX Go

Vertical Tail Side Force = -(Vertical Tail Moment/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 = -(Vertical Tail Moment/Vertical Tail Moment Arm) to calculate the Vertical Tail Side Force, Vertical Tail Side Force for Given Moment is a measure of the force exerted by the vertical tail of an aircraft in response to a moment or turning force, calculated by dividing the moment produced by the vertical tail by the vertical tail moment arm, providing a critical parameter in aircraft design and stability analysis. 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 Vertical Tail Moment (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 -> -4.5 = -(5.4/1.2).

FAQ

What is Vertical Tail Side Force for Given Moment?

Vertical Tail Side Force for Given Moment is a measure of the force exerted by the vertical tail of an aircraft in response to a moment or turning force, calculated by dividing the moment produced by the vertical tail by the vertical tail moment arm, providing a critical parameter in aircraft design and stability analysis and is represented as Y_v = -(N_v/𝒍_v) or Vertical Tail Side Force = -(Vertical Tail Moment/Vertical Tail Moment Arm). Vertical Tail Moment 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?

Vertical Tail Side Force for Given Moment is a measure of the force exerted by the vertical tail of an aircraft in response to a moment or turning force, calculated by dividing the moment produced by the vertical tail by the vertical tail moment arm, providing a critical parameter in aircraft design and stability analysis is calculated using Vertical Tail Side Force = -(Vertical Tail Moment/Vertical Tail Moment Arm). To calculate Vertical Tail Side Force for Given Moment, you need Vertical Tail Moment (N_v) & Vertical Tail Moment Arm (𝒍_v). With our tool, you need to enter the respective value for Vertical Tail Moment & 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 Vertical Tail Moment & 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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