Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Air Resistance Force
Air Resistance=Air Constant*Velocity^2 GO
Archimedes Principle
Archimedes Principle=Density*Acceleration Due To Gravity*Velocity GO
Wavelength Of The Wave(Using Velocity)
Wavelength Of A Wave=Velocity*Time Period Of Progressive Wave GO
Time Period (Using Velocity )
Time Period Of Progressive Wave=Wavelength/Velocity GO
Stokes Force
Stokes Force=6*pi*Radius*Dynamic viscosity*Velocity GO
Angular Frequency (Using Velocity )
Angular Frequency=(2*pi*Velocity)/Wavelength GO
Centripetal Force
Centripetal Force=(Mass*(Velocity)^2)/Radius GO
Frequency Of Wavelength ( Using Velocity )
frequency=Velocity/Wavelength Of A Wave GO
Wave Number (Using Angular Frequency)
Wave Number=Angular Frequency/Velocity GO
Kinetic Energy
Kinetic Energy=(Mass*Velocity^2)/2 GO
Wavelength Of The Wave(Using Frequency)
Wavelength=Velocity/frequency GO

1 Other formulas that calculate the same Output

Wing Mean aerodynamic chord for given horizontal tail volume ratio
Mean aerodynamic chord=Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio) GO

Mean aerodynamic chord for given tail pitching moment coefficient Formula

Mean aerodynamic chord=Pitching moment due to tail/(0.5*Freestream density*(Velocity^2)*Reference Area*Tail pitching moment coefficient)
c<sub>ma</sub>=M<sub>t</sub>/(0.5*ρ<sub>∞</sub>*(v^2)*S*C<sub>m<sub>t</sub></sub>)
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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*(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 and 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 ), Velocity (v), Reference Area (S) and 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 -> 0.000389 = 3/(0.5*1.225*(60^2)*5*0.7).

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*ρ*(v^2)*S*Cmt) or Mean aerodynamic chord=Pitching moment due to tail/(0.5*Freestream density*(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, Velocity, in physics, is a vector quantity (it has both magnitude and direction), and is the time rate of change of position (of an object). , 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 and 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*(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 ), Velocity (v), Reference Area (S) and Tail pitching moment coefficient (Cmt). With our tool, you need to enter the respective value for Pitching moment due to tail, Freestream density, Velocity, Reference Area and 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, Velocity, Reference Area and 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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