Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Tail lift coefficient for given pitching moment coefficient
Tail Lift Coefficient=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm) GO
Tail Pitching moment coefficient for given tail efficiency
Tail pitching moment coefficient=-Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient/(Reference Area*Mean aerodynamic chord) GO
Tail Efficiency for given pitching moment coefficient
Tail Efficiency=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient) GO
Tail area for given tail moment coefficient
Horizontal tail area=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient) GO
Tail lift coefficient for given pitching moment
Tail Lift Coefficient=-2*Pitching moment due to tail/(Horizontal tail moment arm*Freestream density*(Tail Velocity^2)*Horizontal tail area) GO
Tail Pitching moment for given lift coefficient
Pitching moment due to tail=-Horizontal tail moment arm*Tail Lift Coefficient*Freestream density*(Tail Velocity^2)*Horizontal tail area/2 GO
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
Horizontal tail volume ratio
Horizontal Tail Volume Ratio=Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord) GO
Tail lift for given tail pitching moment
Lift due to tail=-Pitching moment due to tail/Horizontal tail moment arm GO
Total Lift of wing-tail combination
Lift force=Lift due to wing+Lift due to tail GO
Lift due to wing only
Lift due to wing=Lift force-Lift due to tail GO

2 Other formulas that calculate the same Output

Tail Pitching moment for given lift coefficient
Pitching moment due to tail=-Horizontal tail moment arm*Tail Lift Coefficient*Freestream density*(Tail Velocity^2)*Horizontal tail area/2 GO
Tail Pitching moment for given moment coefficient
Pitching moment due to tail=Tail pitching moment coefficient*(0.5*Freestream density*(Velocity^2)*Reference Area*Mean aerodynamic chord) GO

Pitching moment due to tail Formula

Pitching moment due to tail=-Horizontal tail moment arm*Lift due to tail
M<sub>t</sub>=-𝒍<sub>t</sub>*L<sub>t</sub>
More formulas
Angle of attack at the tail GO
Angle of attack of the wing GO
Angle of incidence of wing GO
Downwash angle GO
Angle of incidence of tail GO
Total Lift of wing-tail combination GO
Lift due to wing only GO
Lift due to tail only GO
Total Lift Coefficient of wing-tail combination GO
Wing Lift Coefficient of wing-tail combination GO
Tail Lift Coefficient of wing-tail combination GO
Tail Efficiency for given lift coefficients GO
Tail area for given tail efficiency GO
Tail lift for given tail pitching moment GO
Tail Pitching moment for given lift coefficient GO
Tail lift coefficient for given pitching moment GO
Tail Pitching moment coefficient GO
Tail Pitching moment for given moment coefficient GO
Mean aerodynamic chord for given tail pitching moment coefficient GO
Vertical tail moment arm for given yawing moment coefficient GO

Where is the aerodynamic center of a wing?

For symmetric airfoils in subsonic flight, the aerodynamic center is located approximately 25% of the chord from the leading edge of the airfoil. This point is described as the quarter-chord point. The aerodynamic center does not change with variation in the angle of attack.

How to Calculate Pitching moment due to tail?

Pitching moment due to tail calculator uses Pitching moment due to tail=-Horizontal tail moment arm*Lift due to tail to calculate the Pitching moment due to tail, The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity. Pitching moment due to tail and is denoted by Mt symbol.

How to calculate Pitching moment due to tail using this online calculator? To use this online calculator for Pitching moment due to tail, enter Horizontal tail moment arm (𝒍t) and Lift due to tail (Lt) and hit the calculate button. Here is how the Pitching moment due to tail calculation can be explained with given input values -> -4.8 = -0.8*6.

FAQ

What is Pitching moment due to tail?
The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity and is represented as Mt=-𝒍t*Lt or Pitching moment due to tail=-Horizontal tail moment arm*Lift due to tail. The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft and Lift due to tail is the lift force acting on the tail (only) of an aircraft .
How to calculate Pitching moment due to tail?
The Pitching moment due to tail is dependent on the lift generated by the tail alone and the distance between the tail lift center and the aircraft's center of gravity is calculated using Pitching moment due to tail=-Horizontal tail moment arm*Lift due to tail. To calculate Pitching moment due to tail, you need Horizontal tail moment arm (𝒍t) and Lift due to tail (Lt). With our tool, you need to enter the respective value for Horizontal tail moment arm and Lift due to tail 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 Horizontal tail moment arm and Lift due to tail. 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=Tail pitching moment coefficient*(0.5*Freestream density*(Velocity^2)*Reference Area*Mean aerodynamic chord)
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