Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

2 Other formulas that calculate the same Output

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

Tail area for given tail efficiency Formula

Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
S<sub>t</sub>=S*(C<sub>L</sub>-C<sub>L<sub>w</sub></sub>)/(C<sub>L<sub>t</sub></sub>*η)
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
Pitching moment due to tail 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

Does the horizontal stabilizer produce lift?

Yes, but not to contribute to the overall lift affecting the aircraft as a whole. The horizontal stabilizer/elevators use the aerodynamic force of lift to raise or lower the aircraft's nose (“change its pitch”).

How to Calculate Tail area for given tail efficiency?

Tail area for given tail efficiency calculator uses Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency) to calculate the Horizontal tail area, The Tail area for given tail efficiency is a function of total lift coefficient, tail efficiency, tail lift coefficient, and wing lift coefficient. Horizontal tail area and is denoted by St symbol.

How to calculate Tail area for given tail efficiency using this online calculator? To use this online calculator for Tail area for given tail efficiency, enter Reference Area (S), lift coefficient (CL), Wing Lift Coefficient (CLw), Tail Lift Coefficient (CLt) and Tail Efficiency (η) and hit the calculate button. Here is how the Tail area for given tail efficiency calculation can be explained with given input values -> 215.0538 = 5*(10-2)/(0.2*0.93).

FAQ

What is Tail area for given tail efficiency?
The Tail area for given tail efficiency is a function of total lift coefficient, tail efficiency, tail lift coefficient, and wing lift coefficient and is represented as St=S*(CL-CLw)/(CLt*η) or Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency). 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, The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity, Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity. 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 area for given tail efficiency?
The Tail area for given tail efficiency is a function of total lift coefficient, tail efficiency, tail lift coefficient, and wing lift coefficient is calculated using Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency). To calculate Tail area for given tail efficiency, you need Reference Area (S), lift coefficient (CL), Wing Lift Coefficient (CLw), Tail Lift Coefficient (CLt) and Tail Efficiency (η). With our tool, you need to enter the respective value for Reference Area, lift coefficient, Wing Lift Coefficient, Tail Lift Coefficient 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 Horizontal tail area?
In this formula, Horizontal tail area uses Reference Area, lift coefficient, Wing Lift Coefficient, Tail Lift Coefficient and Tail Efficiency. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Horizontal tail area=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
  • Horizontal tail area=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
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