Tail Lift Coefficient of wing-tail combination Solution

STEP 0: Pre-Calculation Summary
Formula Used
Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)
CTlift = S*(CL-CWlift)/(η*St)
This formula uses 6 Variables
Variables Used
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
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 Efficiency - Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
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 Efficiency: 0.92 --> 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
CTlift = S*(CL-CWlift)/(η*St) --> 5.08*(1.108-1.01)/(0.92*1.8)
Evaluating ... ...
CTlift = 0.300628019323672
STEP 3: Convert Result to Output's Unit
0.300628019323672 --> No Conversion Required
FINAL ANSWER
0.300628019323672 0.300628 <-- Tail Lift Coefficient
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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15 Wing-Tail Contribution Calculators

Tail lift coefficient for given pitching moment coefficient
Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm)
Tail lift coefficient for given pitching moment
Go Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area)
Tail Lift Coefficient of wing-tail combination
Go Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)
Tail Efficiency for given lift coefficients
Go Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal tail area)
Tail area for given tail efficiency
Go Horizontal tail area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
Total Lift Coefficient of wing-tail combination
Go Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
Wing Lift Coefficient of wing-tail combination
Go Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
Angle of incidence of wing
Go Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle
Angle of incidence of tail
Go Tail incidence angle = Horizontal tail angle of attack-Wing angle of attack+Wing incidence angle+Downwash angle
Angle of Attack at Tail
Go Horizontal tail angle of attack = Wing angle of attack-Wing incidence angle-Downwash angle+Tail incidence angle
Angle of attack of wing
Go Wing angle of attack = Horizontal tail angle of attack+Wing incidence angle+Downwash angle-Tail incidence angle
Downwash angle
Go Downwash angle = Wing angle of attack-Wing incidence angle-Horizontal tail angle of attack+Tail incidence angle
Total Lift of wing-tail combination
Go Lift Force = Lift due to wing+Lift due to tail
Lift due to wing only
Go Lift due to wing = Lift Force-Lift due to tail
Lift due to tail only
Go Lift due to tail = Lift Force-Lift due to wing

Tail Lift Coefficient of wing-tail combination Formula

Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)
CTlift = S*(CL-CWlift)/(η*St)

What is the tail end of a plane called?

The tail usually has a fixed horizontal piece, called the horizontal stabilizer, and a fixed vertical piece called the vertical stabilizer. The stabilizers' job is to provide stability for the aircraft, to keep it flying straight.

How to Calculate Tail Lift Coefficient of wing-tail combination?

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

How to calculate Tail Lift Coefficient of wing-tail combination using this online calculator? To use this online calculator for Tail Lift Coefficient of wing-tail combination, enter Reference Area (S), Lift Coefficient (CL), Wing Lift Coefficient (CWlift), Tail Efficiency (η) & Horizontal tail area (St) and hit the calculate button. Here is how the Tail Lift Coefficient of wing-tail combination calculation can be explained with given input values -> 0.276087 = 5.08*(1.108-1.01)/(0.92*1.8).

FAQ

What is Tail Lift Coefficient of wing-tail combination?
The Tail Lift Coefficient of wing-tail combination is a function of total lift coefficient, tail efficiency, horizontal tail area, and wing lift coefficient and is represented as CTlift = S*(CL-CWlift)/(η*St) or Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*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 Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing & The Horizontal tail area is the area of the horizontal tail of an aircraft.
How to calculate Tail Lift Coefficient of wing-tail combination?
The Tail Lift Coefficient of wing-tail combination is a function of total lift coefficient, tail efficiency, horizontal tail area, and wing lift coefficient is calculated using Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area). To calculate Tail Lift Coefficient of wing-tail combination, you need Reference Area (S), Lift Coefficient (CL), Wing Lift Coefficient (CWlift), Tail Efficiency (η) & Horizontal tail area (St). With our tool, you need to enter the respective value for Reference Area, Lift Coefficient, Wing Lift Coefficient, Tail Efficiency & Horizontal tail area 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 Reference Area, Lift Coefficient, Wing Lift Coefficient, Tail Efficiency & Horizontal tail area. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • 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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