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Tail Lift Coefficient of Wing-Tail Combination Formula

GoTail Lift Coefficient for given Pitching Moment Formula

GoTail Lift Coefficient for given Pitching Moment Coefficient Formula

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Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity. Check FAQs

CT lift = S \cdot \frac{C L - CW lift}{η \cdot S t}

CT_lift - Tail Lift Coefficient?S - Reference Area?C_L - Lift Coefficient?CW_lift - Wing Lift Coefficient?η - Tail Efficiency?S_t - Horizontal Tail Area?

Tail Lift Coefficient of Wing-Tail Combination Example

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Here is how the Tail Lift Coefficient of Wing-Tail Combination equation looks like with Values.

Here is how the Tail Lift Coefficient of Wing-Tail Combination equation looks like with Units.

Here is how the Tail Lift Coefficient of Wing-Tail Combination equation looks like.

0.3006 = 5.08 \cdot \frac{1.108 - 1.01}{0.92 \cdot 1.8}

0.3006 = 5.08m² \cdot \frac{1.108 - 1.01}{0.92 \cdot 1.8m²}

0.3006 = 5.08 \cdot \frac{1.108 - 1.01}{0.92 \cdot 1.8}

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Tail Lift Coefficient of Wing-Tail Combination Solution

Follow our step by step solution on how to calculate Tail Lift Coefficient of Wing-Tail Combination?

FIRST Step Consider the formula

CT lift = S \cdot \frac{C L - CW lift}{η \cdot S t}

Next Step Substitute values of Variables

∴

CT lift = 5.08m² \cdot \frac{1.108 - 1.01}{0.92 \cdot 1.8m²}

Next Step Prepare to Evaluate

∴

CT lift = 5.08 \cdot \frac{1.108 - 1.01}{0.92 \cdot 1.8}

Next Step Evaluate

∴

CT lift = 0.300628019323672

LAST Step Rounding Answer

∴

CT lift = 0.3006

Tail Lift Coefficient of Wing-Tail Combination Formula Elements

Variables

Tail Lift Coefficient

Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.

Symbol: CT_lift

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Tail Lift Coefficient

Reference 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.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference 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.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Wing Lift Coefficient

Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.

Symbol: CW_lift

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Wing Lift Coefficient

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.

Symbol: η

Measurement: NAUnit: Unitless

Note: Value should be between 0.8 to 1.2.

Formulas to find Tail Efficiency

Horizontal Tail Area

The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.

Symbol: S_t

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Horizontal Tail Area

Other Formulas to find Tail Lift Coefficient

Go Tail Lift Coefficient for given Pitching Moment

CT lift = - 2 \cdot \frac{M t}{𝒍 t \cdot ρ ∞ \cdot {V tail}^{2} \cdot S t}

Go Tail Lift Coefficient for given Pitching Moment Coefficient

CT lift = - (Cm t \cdot S \cdot \frac{c ma}{η \cdot S t \cdot 𝒍 t})

Other formulas in Wing Tail Contribution category

Go Angle of Attack at Tail

α t = α w - 𝒊 w - ε + 𝒊 t

Go Angle of Attack of Wing

α w = α t + 𝒊 w + ε - 𝒊 t

Go Angle of incidence of wing

𝒊 w = α w - α t - ε + 𝒊 t

Go Downwash angle

ε = α w - 𝒊 w - α t + 𝒊 t

How to Evaluate Tail Lift Coefficient of Wing-Tail Combination?

Tail Lift Coefficient of Wing-Tail Combination evaluator uses Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal Tail Area) to evaluate the Tail Lift Coefficient, Tail Lift Coefficient of Wing-Tail Combination is a measure of the aerodynamic efficiency of the wing-tail combination, calculated by considering the reference area, lift coefficients of the wing and horizontal tail, and the tail efficiency, providing a comprehensive understanding of the aircraft's stability. Tail Lift Coefficient is denoted by CT_lift symbol.

How to evaluate Tail Lift Coefficient of Wing-Tail Combination using this online evaluator? To use this online evaluator for Tail Lift Coefficient of Wing-Tail Combination, enter Reference Area (S), Lift Coefficient (C_L), Wing Lift Coefficient (CW_lift), Tail Efficiency (η) & Horizontal Tail Area (S_t) and hit the calculate button.

FAQs on Tail Lift Coefficient of Wing-Tail Combination

What is the formula to find Tail Lift Coefficient of Wing-Tail Combination?

The formula of Tail Lift Coefficient of Wing-Tail Combination is expressed as Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal Tail Area). Here is an example- 0.300628 = 5.08*(1.108-1.01)/(0.92*1.8).

How to calculate Tail Lift Coefficient of Wing-Tail Combination?

With Reference Area (S), Lift Coefficient (C_L), Wing Lift Coefficient (CW_lift), Tail Efficiency (η) & Horizontal Tail Area (S_t) we can find Tail Lift Coefficient of Wing-Tail Combination using the formula - Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal Tail Area).

What are the other ways to Calculate Tail Lift Coefficient?

Here are the different ways to Calculate Tail Lift Coefficient-

Tail Lift Coefficient=-2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^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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Tail Lift Coefficient of Wing-Tail Combination Formula

​GoTail Lift Coefficient for given Pitching Moment Formula

​GoTail Lift Coefficient for given Pitching Moment Coefficient Formula

Tail Lift Coefficient of Wing-Tail Combination Example

Tail Lift Coefficient of Wing-Tail Combination Solution

Tail Lift Coefficient of Wing-Tail Combination Formula Elements

Other Formulas to find Tail Lift Coefficient

Other formulas in Wing Tail Contribution category

How to Evaluate Tail Lift Coefficient of Wing-Tail Combination?

FAQs on Tail Lift Coefficient of Wing-Tail Combination

Variable Name

GoTail Lift Coefficient for given Pitching Moment Formula

GoTail Lift Coefficient for given Pitching Moment Coefficient Formula