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Tail Pitching moment for given moment coefficient Calculator

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✖Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.ⓘ Tail Pitching Moment Coefficient [Cmt]
+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 [cma]
+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 [Mt]
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Formula
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Tail Pitching moment for given moment coefficient

Formula
`"M"_{"t"} = ("Cm"_{"t"}*"ρ"_{"∞"}*"V"^2*"S"*"c"_{"ma"})/2`

Example
`"-218.4273N*m"=("-0.39"*"1.225kg/m³"*("30m/s")^2*"5.08m²"*"0.2m")/2`

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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
Mt = (Cmt*ρ∞*V^2*S*cma)/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
Mt = (Cmt*ρ∞*V^2*S*cma)/2 --> ((-0.39)*1.225*30^2*5.08*0.2)/2
Evaluating ... ...
Mt = -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 00.004 seconds)
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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Tail Contribution » Tail Pitching moment for given moment coefficient

Credits

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 Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 200+ more calculators!

19 Tail Contribution Calculators

Tail Pitching moment coefficient for given tail efficiency
Go Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)
Tail Efficiency for given pitching moment coefficient
Go Tail Efficiency = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient)
Tail moment arm for given tail moment coefficient
Go Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
Tail area for given tail moment coefficient
Go Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
Mean aerodynamic chord for given tail pitching moment coefficient
Go Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)
Tail Pitching moment coefficient
Go Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)
Tail Pitching moment for given moment coefficient
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
Go Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2
Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio)
Wing Reference area for given horizontal tail volume ratio
Go Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)
Horizontal tail volume ratio
Go Horizontal Tail Volume Ratio = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)
Tail moment arm for given horizontal tail volume ratio
Go Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
Horizontal tail area for given tail volume ratio
Go Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
Horizontal tail volume ratio for given pitching moment coefficient
Go Horizontal Tail Volume Ratio = -Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient)
Tail lift coefficient for given tail volume ratio
Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
Tail Efficiency for given tail volume ratio
Go Tail Efficiency = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Lift Coefficient)
Tail Pitching moment coefficient for given tail volume ratio
Go Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient
Tail lift for given tail pitching moment
Go Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm
Pitching moment due to tail
Go Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail

Tail Pitching moment for given moment coefficient Formula

Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)/2
Mt = (Cmt*ρ∞*V^2*S*cma)/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, The Tail Pitching moment for given moment coefficient is a function of the coefficient of pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the mean aerodynamic chord of the wing. Pitching Moment due to Tail is denoted by Mt 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 (Cmt), Freestream Density (ρ∞), Flight Velocity (V), Reference Area (S) & Mean aerodynamic chord (cma) 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?
The Tail Pitching moment for given moment coefficient is a function of the coefficient of pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the mean aerodynamic chord of the wing and is represented as Mt = (Cmt*ρ∞*V^2*S*cma)/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?
The Tail Pitching moment for given moment coefficient is a function of the coefficient of pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the mean aerodynamic chord of the wing 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 (Cmt), Freestream Density (ρ∞), Flight Velocity (V), Reference Area (S) & Mean aerodynamic chord (cma). 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*Tail Velocity^2*Horizontal tail area)/2
  • Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail
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