Tail Efficiency for given lift coefficients 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%
✖The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ Horizontal Tail Area [S_t]			+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 for given lift coefficients [η]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Wing Tail Contribution Formulas PDF PDF Image

Tail Efficiency for given lift coefficients Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
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.

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
Horizontal Tail Area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

η = S*(C_L-CW_lift)/(CT_lift*S_t) --> 5.08*(1.108-1.01)/(0.3*1.8)

Evaluating ... ...

η = 0.921925925925927

STEP 3: Convert Result to Output's Unit

0.921925925925927 --> No Conversion Required

FINAL ANSWER

0.921925925925927 ≈ 0.921926 <-- Tail Efficiency

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Wing Tail Contribution » Tail Efficiency for given lift coefficients

Credits

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

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 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 Efficiency for given lift coefficients Formula

LaTeX Go

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

What is V-tail?

The V-tail or Vee-tail (sometimes called a butterfly tail or Rudlicki's V-tail) of an aircraft is an unconventional arrangement of the tail control surfaces that replaces the traditional fin and horizontal surfaces with two surfaces set in a V-shaped configuration.

How to Calculate Tail Efficiency for given lift coefficients?

Tail Efficiency for given lift coefficients calculator uses Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal Tail Area) to calculate the Tail Efficiency, Tail Efficiency for given Lift Coefficients is a measure of the proportion of the total lift provided by the tail section of an aircraft, considering the reference area, lift coefficients of the tail and wing, and horizontal tail area. Tail Efficiency is denoted by η symbol.

How to calculate Tail Efficiency for given lift coefficients using this online calculator? To use this online calculator for Tail Efficiency for given lift coefficients, enter Reference Area (S), Lift Coefficient (C_L), Wing Lift Coefficient (CW_lift), Tail Lift Coefficient (CT_lift) & Horizontal Tail Area (S_t) and hit the calculate button. Here is how the Tail Efficiency for given lift coefficients calculation can be explained with given input values -> 0.921926 = 5.08*(1.108-1.01)/(0.3*1.8).

FAQ

What is Tail Efficiency for given lift coefficients?

Tail Efficiency for given Lift Coefficients is a measure of the proportion of the total lift provided by the tail section of an aircraft, considering the reference area, lift coefficients of the tail and wing, and horizontal tail area and is represented as η = S*(C_L-CW_lift)/(CT_lift*S_t) or Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal Tail Area). 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 & The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.

How to calculate Tail Efficiency for given lift coefficients?

Tail Efficiency for given Lift Coefficients is a measure of the proportion of the total lift provided by the tail section of an aircraft, considering the reference area, lift coefficients of the tail and wing, and horizontal tail area is calculated using Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal Tail Area). To calculate Tail Efficiency for given lift coefficients, you need Reference Area (S), Lift Coefficient (C_L), Wing Lift Coefficient (CW_lift), Tail Lift Coefficient (CT_lift) & Horizontal Tail Area (S_t). With our tool, you need to enter the respective value for Reference Area, Lift Coefficient, Wing Lift Coefficient, Tail Lift Coefficient & Horizontal Tail Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search