Tail Pitching moment coefficient for given tail volume ratio Calculator

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Static Stability and Control

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Introduction and Governing Equations

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Longitudinal Stability

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Directional Stability

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Fuselage Contribution

Wing-Tail Contribution

✖Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.ⓘ Horizontal Tail Volume Ratio [V_H]			+10% -10%
✖Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.ⓘ Tail Efficiency [η]			+10% -10%
✖Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.ⓘ Tail Lift Coefficient [CT_lift]			+10% -10%

✖Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.ⓘ Tail Pitching moment coefficient for given tail volume ratio [Cm_t]

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Formula

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Tail Pitching moment coefficient for given tail volume ratio

Formula

`"Cm"_{"t"} = -"V"_{"H"}*"η"*"CT"_{"lift"}`

Example

`"-0.39192"=-"1.42"*"0.92"*"0.3"`

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Tail Pitching moment coefficient for given tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient
Cm_t = -V_H*η*CT_lift
This formula uses 4 Variables

Variables Used

Tail Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.
Horizontal Tail Volume Ratio - Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.
Tail Efficiency - Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.

STEP 1: Convert Input(s) to Base Unit

Horizontal Tail Volume Ratio: 1.42 --> No Conversion Required
Tail Efficiency: 0.92 --> No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Cm_t = -V_H*η*CT_lift --> -1.42*0.92*0.3

Evaluating ... ...

Cm_t = -0.39192

STEP 3: Convert Result to Output's Unit

-0.39192 --> No Conversion Required

FINAL ANSWER

-0.39192 <-- Tail Pitching Moment Coefficient

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Tail Contribution » Tail Pitching moment coefficient for given tail volume ratio

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Amrita School of Engineering (ASE), Vallikavu

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< 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

Tail Pitching moment coefficient for given tail volume ratio Formula

Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient
Cm_t = -V_H*η*CT_lift

What airfoil shape produces the greatest lift at low speeds?

The straight-wing is found on a lot of low-speed airplanes. This kind of wing extends from the body of the aircraft at right angles. These wings provide good lift at low speeds, and they are structurally efficient but are not suited to high speeds.

How to Calculate Tail Pitching moment coefficient for given tail volume ratio?

Tail Pitching moment coefficient for given tail volume ratio calculator uses Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient to calculate the Tail Pitching Moment Coefficient, The Tail Pitching moment coefficient for given tail volume ratio is dependent on the tail efficiency, tail volume ratio, and tail lift coefficient. Tail Pitching Moment Coefficient is denoted by Cm_t symbol.

How to calculate Tail Pitching moment coefficient for given tail volume ratio using this online calculator? To use this online calculator for Tail Pitching moment coefficient for given tail volume ratio, enter Horizontal Tail Volume Ratio (V_H), Tail Efficiency (η) & Tail Lift Coefficient (CT_lift) and hit the calculate button. Here is how the Tail Pitching moment coefficient for given tail volume ratio calculation can be explained with given input values -> -0.38766 = -1.42*0.92*0.3.

FAQ

What is Tail Pitching moment coefficient for given tail volume ratio?

The Tail Pitching moment coefficient for given tail volume ratio is dependent on the tail efficiency, tail volume ratio, and tail lift coefficient and is represented as Cm_t = -V_H*η*CT_lift or Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient. Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord, Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing & Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.

How to calculate Tail Pitching moment coefficient for given tail volume ratio?

The Tail Pitching moment coefficient for given tail volume ratio is dependent on the tail efficiency, tail volume ratio, and tail lift coefficient is calculated using Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient. To calculate Tail Pitching moment coefficient for given tail volume ratio, you need Horizontal Tail Volume Ratio (V_H), Tail Efficiency (η) & Tail Lift Coefficient (CT_lift). With our tool, you need to enter the respective value for Horizontal Tail Volume Ratio, Tail Efficiency & Tail Lift Coefficient 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 Tail Pitching Moment Coefficient?

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

Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)
Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)

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