Pitching moment due to tail Calculator

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Static Stability and Control

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Longitudinal Stability

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Wing-Tail Contribution

✖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 is the lift force acting on the tail (only) 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]

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Formula

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Pitching moment due to tail

Formula

`"M"_{"t"} = -"𝒍"_{"t"}*"L"_{"t"}`

Example

`"-218.432N*m"=-"0.8m"*"273.04N"`

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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 is the lift force acting on the tail (only) of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Horizontal tail moment arm: 0.8 Meter --> 0.8 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 --> -0.8*273.04

Evaluating ... ...

M_t = -218.432

STEP 3: Convert Result to Output's Unit

-218.432 Newton Meter --> No Conversion Required

FINAL ANSWER

-218.432 Newton Meter <-- Pitching Moment due to Tail

(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

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

< 19 Tail Contribution Calculators

Tail Pitching moment coefficient for given tail efficiency

Go Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)

Tail Efficiency for given pitching moment coefficient

Go Tail Efficiency = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient)

Tail moment arm for given tail moment coefficient

Go Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)

Tail area for given tail moment coefficient

Go Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)

Mean aerodynamic chord for given tail pitching moment coefficient

Go Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)

Tail Pitching moment coefficient

Go Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)

Tail Pitching moment for given moment coefficient

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

Go Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2

Wing Mean aerodynamic chord for given horizontal tail volume ratio

Go Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio)

Wing Reference area for given horizontal tail volume ratio

Go Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)

Horizontal tail volume ratio

Go Horizontal Tail Volume Ratio = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)

Tail moment arm for given horizontal tail volume ratio

Go Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area

Horizontal tail area for given tail volume ratio

Go Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm

Horizontal tail volume ratio for given pitching moment coefficient

Go Horizontal Tail Volume Ratio = -Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient)

Tail lift coefficient for given tail volume ratio

Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)

Tail Efficiency for given tail volume ratio

Go Tail Efficiency = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Lift Coefficient)

Tail Pitching moment coefficient for given tail volume ratio

Go Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient

Tail lift for given tail pitching moment

Go Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm

Pitching moment due to tail

Go Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail

Pitching moment due to tail Formula

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, The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity. 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 -> -4.8 = -0.8*273.04.

FAQ

What is Pitching moment due to tail?

The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity 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 is the lift force acting on the tail (only) of an aircraft.

How to calculate Pitching moment due to tail?

The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity 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*Tail Velocity^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

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