Tail Pitching Moment for given 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%
✖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%

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Tail Pitching Moment for given Moment Coefficient [M_t]

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Tail Pitching Moment for given Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2
M_t = (Cm_t*ρ_∞*V^2*S*c_ma)/2
This formula uses 6 Variables

Variables Used

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

Tail Pitching Moment Coefficient: -0.39 --> 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

M_t = (Cm_t*ρ_∞*V^2*S*c_ma)/2 --> ((-0.39)*1.225*30^2*5.08*0.2)/2

Evaluating ... ...

M_t = -218.4273

STEP 3: Convert Result to Output's Unit

-218.4273 Newton Meter --> No Conversion Required

FINAL ANSWER

-218.4273 Newton Meter <-- Pitching Moment due to Tail

(Calculation completed in 00.021 seconds)

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Created by Vinay Mishra

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

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Indian Institute of Technology (IIT), Bombay

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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 for given Moment Coefficient Formula

LaTeX Go

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

What is aerodynamic center?

The aerodynamic center is defined to be the point on the chord line of the airfoil at which the pitching moment coefficient does not vary with angle of attack, or at least does not vary significantly over the operating range of angle of attack of the airfoil.

How to Calculate Tail Pitching Moment for given Moment Coefficient?

Tail Pitching Moment for given Moment Coefficient calculator uses Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2 to calculate the Pitching Moment due to Tail, Tail Pitching Moment for given Moment Coefficient is a measure of the rotational force around the lateral axis of an aircraft's tail, calculated by considering the tail pitching moment coefficient, freestream density, velocity, reference area, and mean aerodynamic chord, providing a vital parameter for aircraft stability and control analysis. Pitching Moment due to Tail is denoted by M_t symbol.

How to calculate Tail Pitching Moment for given Moment Coefficient using this online calculator? To use this online calculator for Tail Pitching Moment for given Moment Coefficient, enter Tail Pitching Moment Coefficient (Cm_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 for given Moment Coefficient calculation can be explained with given input values -> -218.4273 = ((-0.39)*1.225*30^2*5.08*0.2)/2.

FAQ

What is Tail Pitching Moment for given Moment Coefficient?

Tail Pitching Moment for given Moment Coefficient is a measure of the rotational force around the lateral axis of an aircraft's tail, calculated by considering the tail pitching moment coefficient, freestream density, velocity, reference area, and mean aerodynamic chord, providing a vital parameter for aircraft stability and control analysis and is represented as M_t = (Cm_t*ρ_∞*V^2*S*c_ma)/2 or Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2. Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, 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 for given Moment Coefficient?

Tail Pitching Moment for given Moment Coefficient is a measure of the rotational force around the lateral axis of an aircraft's tail, calculated by considering the tail pitching moment coefficient, freestream density, velocity, reference area, and mean aerodynamic chord, providing a vital parameter for aircraft stability and control analysis is calculated using Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2. To calculate Tail Pitching Moment for given Moment Coefficient, you need Tail Pitching Moment Coefficient (Cm_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 Tail Pitching Moment Coefficient, 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 Pitching Moment due to Tail?

In this formula, Pitching Moment due to Tail uses Tail Pitching Moment Coefficient, 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 -

Pitching Moment due to Tail = -(Horizontal Tail Moment Arm*Tail Lift Coefficient*Freestream Density*Velocity Tail^2*Horizontal Tail Area)/2
Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail

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