Pitching Moment due to Tail Calculator

✖The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.ⓘ Horizontal Tail Moment Arm [𝒍_t]			+10% -10%
✖Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.ⓘ Lift due to Tail [L_t]			+10% -10%

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Pitching Moment due to Tail [M_t]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Tail Contribution Formulas PDF PDF Image

Pitching Moment due to Tail Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail
M_t = -𝒍_t*L_t
This formula uses 3 Variables

Variables Used

Pitching Moment due to Tail - (Measured in Newton Meter) - Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.
Horizontal Tail Moment Arm - (Measured in Meter) - The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.
Lift due to Tail - (Measured in Newton) - Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Horizontal Tail Moment Arm: 0.801511 Meter --> 0.801511 Meter No Conversion Required
Lift due to Tail: 273.04 Newton --> 273.04 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_t = -𝒍_t*L_t --> -0.801511*273.04

Evaluating ... ...

M_t = -218.84456344

STEP 3: Convert Result to Output's Unit

-218.84456344 Newton Meter --> No Conversion Required

FINAL ANSWER

-218.84456344 ≈ -218.844563 Newton Meter <-- Pitching Moment due to Tail

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Tail Contribution » Pitching Moment due to Tail

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!

< Tail Contribution Calculators

Tail Pitching Moment for given Moment Coefficient

LaTeX Go Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2

Tail Pitching Moment for given Lift Coefficient

LaTeX Go Pitching Moment due to Tail = -(Horizontal Tail Moment Arm*Tail Lift Coefficient*Freestream Density*Velocity Tail^2*Horizontal Tail Area)/2

Tail Lift for given Tail Pitching Moment

LaTeX Go Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm)

Pitching Moment due to Tail

LaTeX Go Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail

Pitching Moment due to Tail Formula

LaTeX Go

Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail
M_t = -𝒍_t*L_t

Where is the aerodynamic center of a wing?

For symmetric airfoils in subsonic flight, the aerodynamic center is located approximately 25% of the chord from the leading edge of the airfoil. This point is described as the quarter-chord point. The aerodynamic center does not change with variation in the angle of attack.

How to Calculate Pitching Moment due to Tail?

Pitching Moment due to Tail calculator uses Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail to calculate the Pitching Moment due to Tail, Pitching Moment due to Tail is a measure of the rotational force that tends to pitch the aircraft nose up or down, calculated as the product of the horizontal tail moment arm and the lift force of the tail, influencing the stability and control of the aircraft during flight. Pitching Moment due to Tail is denoted by M_t symbol.

How to calculate Pitching Moment due to Tail using this online calculator? To use this online calculator for Pitching Moment due to Tail, enter Horizontal Tail Moment Arm (𝒍_t) & Lift due to Tail (L_t) and hit the calculate button. Here is how the Pitching Moment due to Tail calculation can be explained with given input values -> -218.844563 = -0.801511*273.04.

FAQ

What is Pitching Moment due to Tail?

Pitching Moment due to Tail is a measure of the rotational force that tends to pitch the aircraft nose up or down, calculated as the product of the horizontal tail moment arm and the lift force of the tail, influencing the stability and control of the aircraft during flight and is represented as M_t = -𝒍_t*L_t or Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail. The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft & Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

How to calculate Pitching Moment due to Tail?

Pitching Moment due to Tail is a measure of the rotational force that tends to pitch the aircraft nose up or down, calculated as the product of the horizontal tail moment arm and the lift force of the tail, influencing the stability and control of the aircraft during flight is calculated using Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail. To calculate Pitching Moment due to Tail, you need Horizontal Tail Moment Arm (𝒍_t) & Lift due to Tail (L_t). With our tool, you need to enter the respective value for Horizontal Tail Moment Arm & Lift due to Tail 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 Pitching Moment due to Tail?

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

Pitching Moment due to Tail = -(Horizontal Tail Moment Arm*Tail Lift Coefficient*Freestream Density*Velocity Tail^2*Horizontal Tail Area)/2
Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2

Home

FREE PDFs

🔍 Search