Tail Pitching Moment Coefficient for given Tail Efficiency Calculator

✖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%
✖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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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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.
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: 0.801511 Meter --> 0.801511 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*0.801511*0.3)/(5.08*0.2)

Evaluating ... ...

Cm_t = -0.391919945669291

STEP 3: Convert Result to Output's Unit

-0.391919945669291 --> No Conversion Required

FINAL ANSWER

-0.391919945669291 ≈ -0.39192 <-- Tail Pitching Moment Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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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 Pitching Moment Coefficient for given Tail Efficiency Formula

LaTeX Go

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, Tail Pitching Moment Coefficient for given Tail Efficiency is a measure that characterizes the pitching moment generated by the tail section of an aircraft, taking into account the efficiency of the tail, horizontal tail area, moment arm, and lift coefficient, in relation to the reference area and mean aerodynamic chord, providing a comprehensive understanding of the tail's influence on the aircraft's stability and control. 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 -> -0.39192 = -(0.92*1.8*0.801511*0.3)/(5.08*0.2).

FAQ

What is Tail Pitching Moment Coefficient for given Tail Efficiency?

Tail Pitching Moment Coefficient for given Tail Efficiency is a measure that characterizes the pitching moment generated by the tail section of an aircraft, taking into account the efficiency of the tail, horizontal tail area, moment arm, and lift coefficient, in relation to the reference area and mean aerodynamic chord, providing a comprehensive understanding of the tail's influence on the aircraft's stability and control 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control, 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?

Tail Pitching Moment Coefficient for given Tail Efficiency is a measure that characterizes the pitching moment generated by the tail section of an aircraft, taking into account the efficiency of the tail, horizontal tail area, moment arm, and lift coefficient, in relation to the reference area and mean aerodynamic chord, providing a comprehensive understanding of the tail's influence on the aircraft's stability and control 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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