Tail Area 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 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 Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ Tail Area for given Tail Moment Coefficient [S_t]

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Tail Area for given Tail Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Horizontal Tail Area = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord)/(Tail Efficiency*Horizontal Tail Moment Arm*Tail Lift Coefficient)
S_t = -(Cm_t*S*c_ma)/(η*𝒍_t*CT_lift)
This formula uses 7 Variables

Variables Used

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 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 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.

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 Moment Arm: 0.801511 Meter --> 0.801511 Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S_t = -(Cm_t*S*c_ma)/(η*𝒍_t*CT_lift) --> -((-0.39)*5.08*0.2)/(0.92*0.801511*0.3)

Evaluating ... ...

S_t = 1.79118212215808

STEP 3: Convert Result to Output's Unit

1.79118212215808 Square Meter --> No Conversion Required

FINAL ANSWER

1.79118212215808 ≈ 1.791182 Square Meter <-- Horizontal Tail Area

(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 Area for given Tail Moment Coefficient Formula

LaTeX Go

What is Super stall?

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How to Calculate Tail Area for given Tail Moment Coefficient?

Tail Area for given Tail Moment Coefficient calculator uses Horizontal Tail Area = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord)/(Tail Efficiency*Horizontal Tail Moment Arm*Tail Lift Coefficient) to calculate the Horizontal Tail Area, Tail Area for given Tail Moment Coefficient is a measure of the horizontal tail area required to achieve a desired tail moment coefficient, taking into account the reference area, mean aerodynamic chord, tail efficiency, and lift coefficient of the tail, it is a critical calculation in aircraft design, ensuring stability and control during flight. Horizontal Tail Area is denoted by S_t symbol.

How to calculate Tail Area for given Tail Moment Coefficient using this online calculator? To use this online calculator for Tail Area 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 Moment Arm (𝒍_t) & Tail Lift Coefficient (CT_lift) and hit the calculate button. Here is how the Tail Area for given Tail Moment Coefficient calculation can be explained with given input values -> 1.791182 = -((-0.39)*5.08*0.2)/(0.92*0.801511*0.3).

FAQ

What is Tail Area for given Tail Moment Coefficient?

Tail Area for given Tail Moment Coefficient is a measure of the horizontal tail area required to achieve a desired tail moment coefficient, taking into account the reference area, mean aerodynamic chord, tail efficiency, and lift coefficient of the tail, it is a critical calculation in aircraft design, ensuring stability and control during flight and is represented as S_t = -(Cm_t*S*c_ma)/(η*𝒍_t*CT_lift) or Horizontal Tail Area = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord)/(Tail Efficiency*Horizontal Tail Moment Arm*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 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.

How to calculate Tail Area for given Tail Moment Coefficient?

Tail Area for given Tail Moment Coefficient is a measure of the horizontal tail area required to achieve a desired tail moment coefficient, taking into account the reference area, mean aerodynamic chord, tail efficiency, and lift coefficient of the tail, it is a critical calculation in aircraft design, ensuring stability and control during flight is calculated using Horizontal Tail Area = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord)/(Tail Efficiency*Horizontal Tail Moment Arm*Tail Lift Coefficient). To calculate Tail Area 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 Moment Arm (𝒍_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 Moment Arm & 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 Area?

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

Horizontal Tail Area = Horizontal Tail Volume Ratio*Reference Area*Mean Aerodynamic Chord/Horizontal Tail Moment Arm

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