Tail moment arm for given tail moment coefficient Calculator

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Static Stability and Control

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Longitudinal Stability

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Wing-Tail Contribution

✖Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.ⓘ Tail Pitching Moment Coefficient [Cm_t]			+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 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%
✖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 horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.ⓘ Tail moment arm for given tail moment coefficient [𝒍_t]

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Tail moment arm for given tail moment coefficient

Formula

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

Example

`"0.797585m"=-("-0.39"*"5.08m²"*"0.2m")/("0.92"*"1.8m²"*"0.3")`

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Tail moment arm for given tail moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
𝒍_t = -(Cm_t*S*c_ma)/(η*S_t*CT_lift)
This formula uses 7 Variables

Variables Used

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 Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.
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.
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.
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

Tail Pitching Moment Coefficient: -0.39 --> 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
Tail Efficiency: 0.92 --> No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

𝒍_t = -(Cm_t*S*c_ma)/(η*S_t*CT_lift) --> -((-0.39)*5.08*0.2)/(0.92*1.8*0.3)

Evaluating ... ...

𝒍_t = 0.797584541062802

STEP 3: Convert Result to Output's Unit

0.797584541062802 Meter --> No Conversion Required

FINAL ANSWER

0.797584541062802 ≈ 0.797585 Meter <-- Horizontal tail moment arm

(Calculation completed in 00.004 seconds)

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

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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ 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

Tail moment arm for given tail moment coefficient Formula

What is the purpose of a horizontal stabilizer on a plane?

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 Tail moment arm for given tail moment coefficient?

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

How to calculate Tail moment arm for given tail moment coefficient using this online calculator? To use this online calculator for Tail moment arm for given tail moment coefficient, enter Tail Pitching Moment Coefficient (Cm_t), Reference Area (S), Mean aerodynamic chord (c_ma), Tail Efficiency (η), Horizontal tail area (S_t) & Tail Lift Coefficient (CT_lift) and hit the calculate button. Here is how the Tail moment arm for given tail moment coefficient calculation can be explained with given input values -> 0.806349 = -((-0.39)*5.08*0.2)/(0.92*1.8*0.3).

FAQ

What is Tail moment arm for given tail moment coefficient?

The Tail moment arm for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail lift coefficient and is represented as 𝒍_t = -(Cm_t*S*c_ma)/(η*S_t*CT_lift) or Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient). Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, 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, 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 & Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.

How to calculate Tail moment arm for given tail moment coefficient?

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

In this formula, Horizontal tail moment arm uses Tail Pitching Moment Coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail area & Tail Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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