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)
Cmt = Mt/(0.5*ρ*V^2*S*cma)
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: -218.43 Newton Meter --> -218.43 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
Cmt = Mt/(0.5*ρ*V^2*S*cma) --> (-218.43)/(0.5*1.225*30^2*5.08*0.2)
Evaluating ... ...
Cmt = -0.390004820825968
STEP 3: Convert Result to Output's Unit
-0.390004820825968 --> No Conversion Required
FINAL ANSWER
-0.390004820825968 -0.390005 <-- Tail Pitching Moment Coefficient
(Calculation completed in 00.004 seconds)

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 Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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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 coefficient Formula

Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)
Cmt = Mt/(0.5*ρ*V^2*S*cma)

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, The Tail Pitching moment coefficient for a horizontal tail is a function of the pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the mean aerodynamic chord of the wing. Tail Pitching Moment Coefficient is denoted by Cmt 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 (Mt), Freestream Density ), Flight Velocity (V), Reference Area (S) & Mean aerodynamic chord (cma) and hit the calculate button. Here is how the Tail Pitching moment coefficient calculation can be explained with given input values -> -0.600014 = (-218.43)/(0.5*1.225*30^2*5.08*0.2).

FAQ

What is Tail Pitching moment coefficient?
The Tail Pitching moment coefficient for a horizontal tail is a function of the 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 Cmt = Mt/(0.5*ρ*V^2*S*cma) 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?
The Tail Pitching moment coefficient for a horizontal tail is a function of the 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 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 (Mt), Freestream Density ), Flight Velocity (V), Reference Area (S) & Mean aerodynamic chord (cma). 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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