Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna 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 moment arm for given tail moment coefficient
Horizontal tail moment arm=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*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
Mean aerodynamic chord for given tail pitching moment coefficient
Mean aerodynamic chord=Pitching moment due to tail/(0.5*Freestream density*(Velocity^2)*Reference Area*Tail pitching moment coefficient) 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
Tail Lift Coefficient of wing-tail combination
Tail Lift Coefficient=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area) GO
Tail area for given tail efficiency
Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency) GO
Total Lift Coefficient of wing-tail combination
lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) GO
Wing Lift Coefficient of wing-tail combination
Wing Lift Coefficient=lift coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) GO

3 Other formulas that calculate the same Output

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 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 Lift Coefficient of wing-tail combination
Tail Lift Coefficient=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area) GO

Tail lift coefficient for given tail volume ratio Formula

Tail Lift Coefficient=-Tail pitching moment coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
C<sub>L<sub>t</sub></sub>=-C<sub>m<sub>t</sub></sub>/(V<sub>H</sub>*η)
More formulas
Tail Pitching moment coefficient for given tail efficiency GO
Tail moment arm for given tail moment coefficient GO
Tail area for given tail moment coefficient GO
Tail lift coefficient for given pitching moment coefficient GO
Tail Efficiency for given pitching moment coefficient GO
Horizontal tail volume ratio GO
Tail moment arm for given horizontal tail volume ratio GO
Wing Mean aerodynamic chord for given horizontal tail volume ratio GO
Wing Reference area for given horizontal tail volume ratio GO
Horizontal tail area for given tail volume ratio GO
Tail Pitching moment coefficient for given tail volume ratio GO
Horizontal tail volume ratio for given pitching moment coefficient GO
Tail Efficiency for given tail volume ratio GO

What is the difference between maneuverability and controllability?

Controllability of an aircraft is the capability of an aircraft to respond to the pilots' control inputs, and maneuverability is the aircraft's quality that can be easily controlled in the given space region.

How to Calculate Tail lift coefficient for given tail volume ratio?

Tail lift coefficient for given tail volume ratio calculator uses Tail Lift Coefficient=-Tail pitching moment coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency) to calculate the Tail Lift Coefficient, The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency. Tail Lift Coefficient and is denoted by CLt symbol.

How to calculate Tail lift coefficient for given tail volume ratio using this online calculator? To use this online calculator for Tail lift coefficient for given tail volume ratio, enter Tail pitching moment coefficient (Cmt), Horizontal Tail Volume Ratio (VH) and Tail Efficiency (η) and hit the calculate button. Here is how the Tail lift coefficient for given tail volume ratio calculation can be explained with given input values -> -0.684262 = -0.7/(1.1*0.93).

FAQ

What is Tail lift coefficient for given tail volume ratio?
The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency and is represented as CLt=-Cmt/(VH*η) or Tail Lift Coefficient=-Tail pitching moment coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency). Tail pitching moment coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord and Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.
How to calculate Tail lift coefficient for given tail volume ratio?
The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency is calculated using Tail Lift Coefficient=-Tail pitching moment coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency). To calculate Tail lift coefficient for given tail volume ratio, you need Tail pitching moment coefficient (Cmt), Horizontal Tail Volume Ratio (VH) and Tail Efficiency (η). With our tool, you need to enter the respective value for Tail pitching moment coefficient, Horizontal Tail Volume Ratio and Tail Efficiency 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 Lift Coefficient?
In this formula, Tail Lift Coefficient uses Tail pitching moment coefficient, Horizontal Tail Volume Ratio and Tail Efficiency. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • Tail Lift Coefficient=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)
  • Tail Lift Coefficient=-2*Pitching moment due to tail/(Horizontal tail moment arm*Freestream density*(Tail Velocity^2)*Horizontal tail area)
  • Tail Lift Coefficient=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm)
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