Tail Pitching Moment Coefficient Calculator

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Pitching Moment due to Tail [M_t]			+10% -10%
✖Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖Flight Velocity refers to the speed at which an aircraft moves through the air.ⓘ Flight Velocity [V]			+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 [Cm_t]

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Tail Pitching Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)
Cm_t = M_t/(0.5*ρ_∞*V^2*S*c_ma)
This formula uses 6 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.
Pitching Moment due to Tail - (Measured in Newton Meter) - Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Flight Velocity - (Measured in Meter per Second) - Flight Velocity refers to the speed at which an aircraft moves through the air.
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

Pitching Moment due to Tail: -218.6644 Newton Meter --> -218.6644 Newton Meter No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Flight Velocity: 30 Meter per Second --> 30 Meter per Second 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 = M_t/(0.5*ρ_∞*V^2*S*c_ma) --> (-218.6644)/(0.5*1.225*30^2*5.08*0.2)

Evaluating ... ...

Cm_t = -0.39042333993965

STEP 3: Convert Result to Output's Unit

-0.39042333993965 --> No Conversion Required

FINAL ANSWER

-0.39042333993965 ≈ -0.390423 <-- Tail Pitching Moment Coefficient

(Calculation completed in 00.014 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Tail Contribution » Tail Pitching Moment Coefficient

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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 Pitching Moment Coefficient Formula

LaTeX Go

Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)
Cm_t = M_t/(0.5*ρ_∞*V^2*S*c_ma)

Why is the mean aerodynamic chord important?

To provide a characteristic figure that can be compared among various wing shapes, the mean aerodynamic chord (abbreviated MAC) is used, although it is complex to calculate. The mean aerodynamic chord is important in determining the amount of aerodynamic lift that a particular wing design will generate.

How to Calculate Tail Pitching Moment Coefficient?

Tail Pitching Moment Coefficient calculator uses Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord) to calculate the Tail Pitching Moment Coefficient, Tail Pitching Moment Coefficient is a measure of the rotational force around the vertical axis of an aircraft's tail, normalized by the freestream dynamic density and reference area, it represents the stabilizing or destabilizing effect of the tail on the aircraft's pitch, providing a critical indicator of the aircraft's stability and control characteristics. Tail Pitching Moment Coefficient is denoted by Cm_t symbol.

How to calculate Tail Pitching Moment Coefficient using this online calculator? To use this online calculator for Tail Pitching Moment Coefficient, enter Pitching Moment due to Tail (M_t), Freestream Density (ρ_∞), Flight Velocity (V), Reference Area (S) & Mean Aerodynamic Chord (c_ma) and hit the calculate button. Here is how the Tail Pitching Moment Coefficient calculation can be explained with given input values -> -0.390423 = (-218.6644)/(0.5*1.225*30^2*5.08*0.2).

FAQ

What is Tail Pitching Moment Coefficient?

Tail Pitching Moment Coefficient is a measure of the rotational force around the vertical axis of an aircraft's tail, normalized by the freestream dynamic density and reference area, it represents the stabilizing or destabilizing effect of the tail on the aircraft's pitch, providing a critical indicator of the aircraft's stability and control characteristics and is represented as Cm_t = M_t/(0.5*ρ_∞*V^2*S*c_ma) or Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord). Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity, Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, Flight Velocity refers to the speed at which an aircraft moves through the air, 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?

Tail Pitching Moment Coefficient is a measure of the rotational force around the vertical axis of an aircraft's tail, normalized by the freestream dynamic density and reference area, it represents the stabilizing or destabilizing effect of the tail on the aircraft's pitch, providing a critical indicator of the aircraft's stability and control characteristics is calculated using Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord). To calculate Tail Pitching Moment Coefficient, you need Pitching Moment due to Tail (M_t), Freestream Density (ρ_∞), Flight Velocity (V), Reference Area (S) & Mean Aerodynamic Chord (c_ma). With our tool, you need to enter the respective value for Pitching Moment due to Tail, Freestream Density, Flight Velocity, 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 Pitching Moment due to Tail, Freestream Density, Flight Velocity, 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 = -(Tail Efficiency*Horizontal Tail Area*Horizontal Tail Moment Arm*Tail Lift Coefficient)/(Reference Area*Mean Aerodynamic Chord)
Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient

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