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Tail Lift Coefficient for given Pitching Moment Coefficient Formula

GoTail Lift Coefficient of Wing-Tail Combination Formula

GoTail Lift Coefficient for given Pitching Moment 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 = - (Cm t \cdot S \cdot \frac{c ma}{η \cdot S t \cdot 𝒍 t})

CT_lift - Tail Lift Coefficient?Cm_t - Tail Pitching Moment Coefficient?S - Reference Area?c_ma - Mean Aerodynamic Chord?η - Tail Efficiency?S_t - Horizontal Tail Area?𝒍_t - Horizontal Tail Moment Arm?

Tail Lift Coefficient for given Pitching Moment Coefficient Example

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Here is how the Tail Lift Coefficient for given Pitching Moment Coefficient equation looks like with Values.

Here is how the Tail Lift Coefficient for given Pitching Moment Coefficient equation looks like with Units.

Here is how the Tail Lift Coefficient for given Pitching Moment Coefficient equation looks like.

0.2985 = - (-0.39 \cdot 5.08 \cdot \frac{0.2}{0.92 \cdot 1.8 \cdot 0.8015})

0.2985 = - (-0.39 \cdot 5.08m² \cdot \frac{0.2m}{0.92 \cdot 1.8m² \cdot 0.8015m})

0.2985 = - (-0.39 \cdot 5.08 \cdot \frac{0.2}{0.92 \cdot 1.8 \cdot 0.8015})

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Tail Lift Coefficient for given Pitching Moment Coefficient Solution

Follow our step by step solution on how to calculate Tail Lift Coefficient for given Pitching Moment Coefficient?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

CT lift = - (-0.39 \cdot 5.08m² \cdot \frac{0.2m}{0.92 \cdot 1.8m² \cdot 0.8015m})

Next Step Prepare to Evaluate

∴

CT lift = - (-0.39 \cdot 5.08 \cdot \frac{0.2}{0.92 \cdot 1.8 \cdot 0.8015})

Next Step Evaluate

∴

CT lift = 0.298530353693013

LAST Step Rounding Answer

∴

CT lift = 0.2985

Tail Lift Coefficient for given Pitching Moment Coefficient 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

Tail Pitching Moment Coefficient

Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.

Symbol: Cm_t

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Tail Pitching Moment 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

Mean Aerodynamic Chord

The Mean Aerodynamic Chord is a two-dimensional representation of the whole wing.

Symbol: c_ma

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Mean Aerodynamic Chord

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

Horizontal Tail Moment Arm

The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.

Symbol: 𝒍_t

Measurement: LengthUnit: m

Note: Value can be positive or negative.

Formulas to find Horizontal Tail Moment Arm

Other Formulas to find Tail Lift Coefficient

Go Tail Lift Coefficient of Wing-Tail Combination

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

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}

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

How to Evaluate Tail Lift Coefficient for given Pitching Moment Coefficient?

Tail Lift Coefficient for given Pitching Moment Coefficient evaluator uses Tail Lift Coefficient = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord/(Tail Efficiency*Horizontal Tail Area*Horizontal Tail Moment Arm)) to evaluate the Tail Lift Coefficient, Tail Lift Coefficient for given Pitching Moment Coefficient is a measure of the tail's ability to counteract the pitching moment, calculated as the product of the tail pitching moment coefficient, reference area and mean aerodynamic chord, divided by the tail efficiency, horizontal tail area, and horizontal tail moment arm. Tail Lift Coefficient is denoted by CT_lift symbol.

How to evaluate Tail Lift Coefficient for given Pitching Moment Coefficient using this online evaluator? To use this online evaluator 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.

FAQs on Tail Lift Coefficient for given Pitching Moment Coefficient

What is the formula to find Tail Lift Coefficient for given Pitching Moment Coefficient?

The formula of Tail Lift Coefficient for given Pitching Moment Coefficient is expressed as Tail Lift Coefficient = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord/(Tail Efficiency*Horizontal Tail Area*Horizontal Tail Moment Arm)). Here is an example- 0.29853 = -((-0.39)*5.08*0.2/(0.92*1.8*0.801511)).

How to calculate Tail Lift Coefficient for given Pitching Moment Coefficient?

With 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) we can find Tail Lift Coefficient for given Pitching Moment Coefficient using the formula - Tail Lift Coefficient = -(Tail Pitching Moment Coefficient*Reference Area*Mean Aerodynamic Chord/(Tail Efficiency*Horizontal Tail Area*Horizontal Tail Moment Arm)).

What are the other ways to Calculate Tail Lift Coefficient?

Here are the different ways to Calculate Tail Lift Coefficient-

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*Velocity Tail^2*Horizontal Tail Area)

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Tail Lift Coefficient for given Pitching Moment Coefficient Formula

​GoTail Lift Coefficient of Wing-Tail Combination Formula

​GoTail Lift Coefficient for given Pitching Moment Formula

Tail Lift Coefficient for given Pitching Moment Coefficient Example

Tail Lift Coefficient for given Pitching Moment Coefficient Solution

Tail Lift Coefficient for given Pitching Moment Coefficient Formula Elements

Other Formulas to find Tail Lift Coefficient

Other formulas in Wing Tail Contribution category

How to Evaluate Tail Lift Coefficient for given Pitching Moment Coefficient?

FAQs on Tail Lift Coefficient for given Pitching Moment Coefficient

Variable Name

GoTail Lift Coefficient of Wing-Tail Combination Formula

GoTail Lift Coefficient for given Pitching Moment Formula