Tail Pitching moment coefficient for given tail efficiency Calculator

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Static Stability and Control

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Longitudinal Stability

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Wing-Tail Contribution

✖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%
✖The Horizontal tail area is the area of the horizontal tail of an aircraft.ⓘ Horizontal tail area [S_t]			+10% -10%
✖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%
✖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%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖The Mean aerodynamic chord is a two-dimensional representation of the whole wing.ⓘ Mean aerodynamic chord [c_ma]			+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 efficiency [Cm_t]

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Formula

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Tail Pitching moment coefficient for given tail efficiency

Formula

`"Cm"_{"t"} = -("η"*"S"_{"t"}*"𝒍"_{"t"}*"CT"_{"lift"})/("S"*"c"_{"ma"})`

Example

`"-0.391181"=-("0.92"*"1.8m²"*"0.8m"*"0.3")/("5.08m²"*"0.2m")`

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Tail Pitching moment coefficient for given tail efficiency Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)
Cm_t = -(η*S_t*𝒍_t*CT_lift)/(S*c_ma)
This formula uses 7 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.
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.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
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.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.

STEP 1: Convert Input(s) to Base Unit

Tail Efficiency: 0.92 --> No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Mean aerodynamic chord: 0.2 Meter --> 0.2 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Cm_t = -(η*S_t*𝒍_t*CT_lift)/(S*c_ma) --> -(0.92*1.8*0.8*0.3)/(5.08*0.2)

Evaluating ... ...

Cm_t = -0.391181102362205

STEP 3: Convert Result to Output's Unit

-0.391181102362205 --> No Conversion Required

FINAL ANSWER

-0.391181102362205 ≈ -0.391181 <-- 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 efficiency

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Created by Vinay Mishra

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

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PSG College of Technology (PSGCT), Coimbatore

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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 efficiency Formula

What is the advantage of T empennage?

Responsive pitch control is crucial for aircraft flying at low speed to allow effective rotation on landing. This configuration also allows high-performance aerodynamics and an excellent glide ratio as the empennage is less affected by the wing and fuselage slipstream.

How to Calculate Tail Pitching moment coefficient for given tail efficiency?

Tail Pitching moment coefficient for given tail efficiency calculator uses Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord) to calculate the Tail Pitching Moment Coefficient, The Tail Pitching moment coefficient for given tail efficiency is a function of the tail efficiency, tail area, moment arm, tail lift coefficient, wing reference area, and mean aerodynamic chord of the wing. Tail Pitching Moment Coefficient is denoted by Cm_t symbol.

How to calculate Tail Pitching moment coefficient for given tail efficiency using this online calculator? To use this online calculator for Tail Pitching moment coefficient for given tail efficiency, enter Tail Efficiency (η), Horizontal tail area (S_t), Horizontal tail moment arm (𝒍_t), Tail Lift Coefficient (CT_lift), Reference Area (S) & Mean aerodynamic chord (c_ma) and hit the calculate button. Here is how the Tail Pitching moment coefficient for given tail efficiency calculation can be explained with given input values -> -0.391181 = -(0.92*1.8*0.8*0.3)/(5.08*0.2).

FAQ

What is Tail Pitching moment coefficient for given tail efficiency?

The Tail Pitching moment coefficient for given tail efficiency is a function of the tail efficiency, tail area, moment arm, tail lift coefficient, wing reference area, and mean aerodynamic chord of the wing and is represented as Cm_t = -(η*S_t*𝒍_t*CT_lift)/(S*c_ma) or Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord). Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing, The Horizontal tail area is the area of the horizontal tail of an aircraft, The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft, Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & The Mean aerodynamic chord is a two-dimensional representation of the whole wing.

How to calculate Tail Pitching moment coefficient for given tail efficiency?

The Tail Pitching moment coefficient for given tail efficiency is a function of the tail efficiency, tail area, moment arm, tail lift coefficient, wing reference area, and mean aerodynamic chord of the wing is calculated using Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord). To calculate Tail Pitching moment coefficient for given tail efficiency, you need Tail Efficiency (η), Horizontal tail area (S_t), Horizontal tail moment arm (𝒍_t), Tail Lift Coefficient (CT_lift), Reference Area (S) & Mean aerodynamic chord (c_ma). With our tool, you need to enter the respective value for Tail Efficiency, Horizontal tail area, Horizontal tail moment arm, Tail Lift Coefficient, Reference Area & Mean aerodynamic chord 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 Tail Efficiency, Horizontal tail area, Horizontal tail moment arm, Tail Lift Coefficient, Reference Area & Mean aerodynamic chord. 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 = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient

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