Tail area for given tail efficiency Calculator

✖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.ⓘ Reference Area [S]			+10% -10%
✖The Lift Coefficient 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.ⓘ Lift Coefficient [C_L]			+10% -10%
✖Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.ⓘ Wing Lift Coefficient [CW_lift]			+10% -10%
✖Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.ⓘ Tail Lift Coefficient [CT_lift]			+10% -10%
✖Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.ⓘ Tail Efficiency [η]			+10% -10%

✖The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ Tail area for given tail efficiency [S_t]

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Tail area for given tail efficiency Solution

STEP 0: Pre-Calculation Summary

Formula Used

Horizontal Tail Area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
S_t = S*(C_L-CW_lift)/(CT_lift*η)
This formula uses 6 Variables

Variables Used

Horizontal Tail Area - (Measured in Square Meter) - The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.
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.
Lift Coefficient - The Lift Coefficient 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 - Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
Tail Efficiency - Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.

STEP 1: Convert Input(s) to Base Unit

Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Lift Coefficient: 1.108 --> No Conversion Required
Wing Lift Coefficient: 1.01 --> No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required
Tail Efficiency: 0.92 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S_t = S*(C_L-CW_lift)/(CT_lift*η) --> 5.08*(1.108-1.01)/(0.3*0.92)

Evaluating ... ...

S_t = 1.80376811594203

STEP 3: Convert Result to Output's Unit

1.80376811594203 Square Meter --> No Conversion Required

FINAL ANSWER

1.80376811594203 ≈ 1.803768 Square Meter <-- Horizontal Tail Area

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Wing Tail Contribution » Tail area for given tail efficiency

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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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< Wing Tail Contribution Calculators

Angle of incidence of wing

LaTeX Go Wing Incidence Angle = Wing Angle of Attack-Horizontal Tail Angle of Attack-Downwash Angle+Tail Incidence Angle

Angle of Attack at Tail

LaTeX Go Horizontal Tail Angle of Attack = Wing Angle of Attack-Wing Incidence Angle-Downwash Angle+Tail Incidence Angle

Angle of Attack of Wing

LaTeX Go Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle

Downwash angle

LaTeX Go Downwash Angle = Wing Angle of Attack-Wing Incidence Angle-Horizontal Tail Angle of Attack+Tail Incidence Angle

Tail area for given tail efficiency Formula

LaTeX Go

Horizontal Tail Area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
S_t = S*(C_L-CW_lift)/(CT_lift*η)

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, Tail Area for given Tail Efficiency is a measure of the horizontal tail area required to maintain stability, calculated by dividing the product of the reference area and the difference between the lift coefficient and the wing's lift coefficient by the product of the tail's lift coefficient and tail efficiency. Horizontal Tail Area is denoted by S_t 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 (C_L), Wing Lift Coefficient (CW_lift), Tail Lift Coefficient (CT_lift) & 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 -> 1.803768 = 5.08*(1.108-1.01)/(0.3*0.92).

FAQ

What is Tail area for given tail efficiency?

Tail Area for given Tail Efficiency is a measure of the horizontal tail area required to maintain stability, calculated by dividing the product of the reference area and the difference between the lift coefficient and the wing's lift coefficient by the product of the tail's lift coefficient and tail efficiency and is represented as S_t = S*(C_L-CW_lift)/(CT_lift*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 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 & 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?

Tail Area for given Tail Efficiency is a measure of the horizontal tail area required to maintain stability, calculated by dividing the product of the reference area and the difference between the lift coefficient and the wing's lift coefficient by the product of the tail's lift coefficient and tail efficiency 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 (C_L), Wing Lift Coefficient (CW_lift), Tail Lift Coefficient (CT_lift) & Tail Efficiency (η). With our tool, you need to enter the respective value for Reference Area, Lift Coefficient, Wing Lift Coefficient, Tail Lift Coefficient & Tail Efficiency and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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