Tail Moment Arm for given Tail Moment Coefficient Calculator

✖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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ 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 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.
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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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

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< 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

Tail Moment Arm for given Tail Moment Coefficient Formula

LaTeX Go

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, Tail Moment Arm for given Tail Moment Coefficient is a measure that calculates the distance from the aircraft's center of gravity to the aerodynamic center, considering the tail's pitching moment coefficient, reference area, mean aerodynamic chord, efficiency, and lift coefficient, this calculation is essential in aircraft design to determine the tail's contribution to the overall stability and control of the aircraft. 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 -> 0.797585 = -((-0.39)*5.08*0.2)/(0.92*1.8*0.3).

FAQ

What is Tail Moment Arm for given Tail Moment Coefficient?

Tail Moment Arm for given Tail Moment Coefficient is a measure that calculates the distance from the aircraft's center of gravity to the aerodynamic center, considering the tail's pitching moment coefficient, reference area, mean aerodynamic chord, efficiency, and lift coefficient, this calculation is essential in aircraft design to determine the tail's contribution to the overall stability and control of the aircraft 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control & 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?

Tail Moment Arm for given Tail Moment Coefficient is a measure that calculates the distance from the aircraft's center of gravity to the aerodynamic center, considering the tail's pitching moment coefficient, reference area, mean aerodynamic chord, efficiency, and lift coefficient, this calculation is essential in aircraft design to determine the tail's contribution to the overall stability and control of the aircraft 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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