Mean Aerodynamic Chord for given 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%
✖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%

✖The Mean Aerodynamic Chord is a two-dimensional representation of the whole wing.ⓘ Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient [c_ma]

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Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mean Aerodynamic Chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)
c_ma = M_t/(0.5*ρ_∞*V^2*S*Cm_t)
This formula uses 6 Variables

Variables Used

Mean Aerodynamic Chord - (Measured in Meter) - The Mean Aerodynamic Chord is a two-dimensional representation of the whole wing.
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.
Tail Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.

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
Tail Pitching Moment Coefficient: -0.39 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c_ma = M_t/(0.5*ρ_∞*V^2*S*Cm_t) --> (-218.6644)/(0.5*1.225*30^2*5.08*(-0.39))

Evaluating ... ...

c_ma = 0.200217097404949

STEP 3: Convert Result to Output's Unit

0.200217097404949 Meter --> No Conversion Required

FINAL ANSWER

0.200217097404949 ≈ 0.200217 Meter <-- Mean Aerodynamic Chord

(Calculation completed in 00.020 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Tail Contribution » Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient

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Created by Vinay Mishra

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

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Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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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

Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient Formula

LaTeX Go

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

What is neutral point in aircraft?

The neutral point is defined, in the pitch plane, as that point on the longitudinal axis of the configuration where the pitching moment does not vary with the angle of attack. Its use is limited to static stability considerations.

How to Calculate Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient?

Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient calculator uses Mean Aerodynamic Chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient) to calculate the Mean Aerodynamic Chord, Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient is a measure of the average distance from the root of the tail to the centroid of the tail, calculated based on the pitching moment coefficient of the tail, freestream density, velocity, reference area, and tail pitching moment coefficient, which is essential in understanding the stability and control of an aircraft during flight. Mean Aerodynamic Chord is denoted by c_ma symbol.

How to calculate Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient using this online calculator? To use this online calculator for Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient, enter Pitching Moment due to Tail (M_t), Freestream Density (ρ_∞), Flight Velocity (V), Reference Area (S) & Tail Pitching Moment Coefficient (Cm_t) and hit the calculate button. Here is how the Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient calculation can be explained with given input values -> 0.200217 = (-218.6644)/(0.5*1.225*30^2*5.08*(-0.39)).

FAQ

What is Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient?

Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient is a measure of the average distance from the root of the tail to the centroid of the tail, calculated based on the pitching moment coefficient of the tail, freestream density, velocity, reference area, and tail pitching moment coefficient, which is essential in understanding the stability and control of an aircraft during flight and is represented as c_ma = M_t/(0.5*ρ_∞*V^2*S*Cm_t) or Mean Aerodynamic Chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient). 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 & Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.

How to calculate Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient?

Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient is a measure of the average distance from the root of the tail to the centroid of the tail, calculated based on the pitching moment coefficient of the tail, freestream density, velocity, reference area, and tail pitching moment coefficient, which is essential in understanding the stability and control of an aircraft during flight is calculated using Mean Aerodynamic Chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient). To calculate Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient, you need Pitching Moment due to Tail (M_t), Freestream Density (ρ_∞), Flight Velocity (V), Reference Area (S) & Tail Pitching Moment Coefficient (Cm_t). With our tool, you need to enter the respective value for Pitching Moment due to Tail, Freestream Density, Flight Velocity, Reference Area & Tail Pitching Moment Coefficient 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 Mean Aerodynamic Chord?

In this formula, Mean Aerodynamic Chord uses Pitching Moment due to Tail, Freestream Density, Flight Velocity, Reference Area & Tail Pitching Moment Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Mean Aerodynamic Chord = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*Horizontal Tail Volume Ratio)

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