Vertical Tail Moment Arm for given Side Force 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%
✖Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.ⓘ Vertical Tail Side Force [Y_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 for given Side Force [𝒍_v]

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Vertical Tail Moment Arm for given Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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 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 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: 5.4 Newton Meter --> 5.4 Newton 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

𝒍_v = -N_v/Y_v --> -5.4/(-4.235)

Evaluating ... ...

𝒍_v = 1.27508854781582

STEP 3: Convert Result to Output's Unit

1.27508854781582 Meter --> No Conversion Required

FINAL ANSWER

1.27508854781582 ≈ 1.275089 Meter <-- Vertical Tail Moment Arm

(Calculation completed in 00.004 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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< 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 Moment Arm for given Side Force Formula

LaTeX Go

Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force
𝒍_v = -N_v/Y_v

What part of an aircraft that helps stabilize or have horizontal stability?

At the rear of the fuselage of most aircraft one finds a horizontal stabilizer and an elevator. The stabilizer is a fixed-wing section whose job is to provide stability for the aircraft, to keep it flying straight. The horizontal stabilizer prevents up-and-down, or pitching, the motion of the aircraft nose.

How to Calculate Vertical Tail Moment Arm for given Side Force?

Vertical Tail Moment Arm for given Side Force calculator uses Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force to calculate the Vertical Tail Moment Arm, Vertical Tail Moment Arm for Given Side Force is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by dividing the moment produced by the vertical tail by the vertical tail side force, providing crucial information for aircraft design and stability analysis. Vertical Tail Moment Arm is denoted by 𝒍_v symbol.

How to calculate Vertical Tail Moment Arm for given Side Force using this online calculator? To use this online calculator for Vertical Tail Moment Arm for given Side Force, enter Vertical Tail Moment (N_v) & Vertical Tail Side Force (Y_v) and hit the calculate button. Here is how the Vertical Tail Moment Arm for given Side Force calculation can be explained with given input values -> 1.275089 = -5.4/(-4.235).

FAQ

What is Vertical Tail Moment Arm for given Side Force?

Vertical Tail Moment Arm for Given Side Force is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by dividing the moment produced by the vertical tail by the vertical tail side force, providing crucial information for aircraft design and stability analysis and is represented as 𝒍_v = -N_v/Y_v or Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force. Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it & Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.

How to calculate Vertical Tail Moment Arm for given Side Force?

Vertical Tail Moment Arm for Given Side Force is a measure of the distance from the vertical tail's aerodynamic center to the aircraft's center of gravity, calculated by dividing the moment produced by the vertical tail by the vertical tail side force, providing crucial information for aircraft design and stability analysis is calculated using Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force. To calculate Vertical Tail Moment Arm for given Side Force, you need Vertical Tail Moment (N_v) & Vertical Tail Side Force (Y_v). With our tool, you need to enter the respective value for Vertical Tail Moment & 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 Arm?

In this formula, Vertical Tail Moment Arm uses Vertical Tail Moment & Vertical Tail Side Force. We can use 3 other way(s) to calculate the same, which is/are as follows -

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 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 Moment Arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical Tail Area

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