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)
cma = Mt/(0.5*ฯโˆž*V^2*S*Cmt)
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: -218.43 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
Tail Pitching Moment Coefficient: -0.39 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
cma = Mt/(0.5*ฯโˆž*V^2*S*Cmt) --> (-218.43)/(0.5*1.225*30^2*5.08*(-0.39))
Evaluating ... ...
cma = 0.200002472218445
STEP 3: Convert Result to Output's Unit
0.200002472218445 Meter --> No Conversion Required
FINAL ANSWER
0.200002472218445 โ‰ˆ 0.200002 Meter <-- Mean aerodynamic chord
(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 Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna 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

Mean aerodynamic chord for given tail pitching moment coefficient Formula

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

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, The Mean aerodynamic chord for given tail pitching moment coefficient is a function of the pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the tail's pitching moment coefficient. Mean aerodynamic chord is denoted by cma 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 (Mt), Freestream Density (ฯโˆž), Flight Velocity (V), Reference Area (S) & Tail Pitching Moment Coefficient (Cmt) 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 -> 0.200002 = (-218.43)/(0.5*1.225*30^2*5.08*(-0.39)).

FAQ

What is Mean aerodynamic chord for given tail pitching moment coefficient?
The Mean aerodynamic chord for given tail pitching moment coefficient is a function of the pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the tail's pitching moment coefficient and is represented as cma = Mt/(0.5*ฯโˆž*V^2*S*Cmt) 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?
The Mean aerodynamic chord for given tail pitching moment coefficient is a function of the pitching moment of the tail, the altitude of the aircraft, the wing's velocity, and the tail's pitching moment coefficient 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 (Mt), Freestream Density (ฯโˆž), Flight Velocity (V), Reference Area (S) & Tail Pitching Moment Coefficient (Cmt). 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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