Tail lift coefficient for given pitching moment coefficient Calculator

↳

⤿

Static Stability and Control

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

⤿

Longitudinal Stability

Directional Control

Directional Stability

Lateral Control

Lateral Stability

Longitudinal Control

⤿

Wing-Tail Contribution

Fuselage Contribution

Tail Contribution

✖Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.ⓘ Tail Pitching Moment Coefficient [Cm_t]			+10% -10%
✖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 Mean aerodynamic chord is a two-dimensional representation of the whole wing.ⓘ Mean aerodynamic chord [c_ma]			+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 area of the horizontal tail of an aircraft.ⓘ Horizontal tail area [S_t]			+10% -10%
✖The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.ⓘ Horizontal tail moment arm [𝒍_t]			+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 for given pitching moment coefficient [CT_lift]

⎘ Copy

👎

Formula

✖

Tail lift coefficient for given pitching moment coefficient

Formula

`"CT"_{"lift"} = -"Cm"_{"t"}*"S"*"c"_{"ma"}/("η"*"S"_{"t"}*"𝒍"_{"t"})`

Example

`"0.299094"=-"-0.39"*"5.08m²"*"0.2m"/("0.92"*"1.8m²"*"0.8m")`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

Tail lift coefficient for given pitching moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm)
CT_lift = -Cm_t*S*c_ma/(η*S_t*𝒍_t)
This formula uses 7 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.
Tail Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.
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.
Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.
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.
Horizontal tail moment arm - (Measured in Meter) - The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.

STEP 1: Convert Input(s) to Base Unit

Tail Pitching Moment Coefficient: -0.39 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Mean aerodynamic chord: 0.2 Meter --> 0.2 Meter No Conversion Required
Tail Efficiency: 0.92 --> No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

CT_lift = -Cm_t*S*c_ma/(η*S_t*𝒍_t) --> -(-0.39)*5.08*0.2/(0.92*1.8*0.8)

Evaluating ... ...

CT_lift = 0.299094202898551

STEP 3: Convert Result to Output's Unit

0.299094202898551 --> No Conversion Required

FINAL ANSWER

0.299094202898551 ≈ 0.299094 <-- Tail Lift Coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Wing-Tail Contribution » Tail lift coefficient for given pitching moment coefficient

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!

< 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 for given pitching moment coefficient Formula

What is elevator deflection?

An elevator is flap-like and is deflected up and down. With this deflection, the camber of the tail's airfoil is changed, and consequently, the tail lift coefficient is changed.

How to Calculate Tail lift coefficient for given pitching moment coefficient?

Tail lift coefficient for given pitching moment coefficient calculator uses Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm) to calculate the Tail Lift Coefficient, The Tail lift coefficient for given pitching moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail moment arm. Tail Lift Coefficient is denoted by CT_lift symbol.

How to calculate Tail lift coefficient for given pitching moment coefficient using this online calculator? To use this online calculator for Tail lift coefficient for given pitching moment coefficient, enter Tail Pitching Moment Coefficient (Cm_t), Reference Area (S), Mean aerodynamic chord (c_ma), Tail Efficiency (η), Horizontal tail area (S_t) & Horizontal tail moment arm (𝒍_t) and hit the calculate button. Here is how the Tail lift coefficient for given pitching moment coefficient calculation can be explained with given input values -> 0.302381 = -(-0.39)*5.08*0.2/(0.92*1.8*0.8).

FAQ

What is Tail lift coefficient for given pitching moment coefficient?

The Tail lift coefficient for given pitching moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail moment arm and is represented as CT_lift = -Cm_t*S*c_ma/(η*S_t*𝒍_t) or Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm). Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, 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 Mean aerodynamic chord is a two-dimensional representation of the whole wing, 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 & The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.

How to calculate Tail lift coefficient for given pitching moment coefficient?

The Tail lift coefficient for given pitching moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail moment arm is calculated using Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm). To calculate Tail lift coefficient for given pitching moment coefficient, you need Tail Pitching Moment Coefficient (Cm_t), Reference Area (S), Mean aerodynamic chord (c_ma), Tail Efficiency (η), Horizontal tail area (S_t) & Horizontal tail moment arm (𝒍_t). With our tool, you need to enter the respective value for Tail Pitching Moment Coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail area & Horizontal tail moment arm 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, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail area & Horizontal tail moment arm. We can use 2 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)

Home

FREE PDFs

🔍 Search