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Tail Lift Coefficient for given Pitching Moment Formula

GoTail Lift Coefficient of Wing-Tail Combination 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 = - 2 \cdot \frac{M t}{𝒍 t \cdot ρ ∞ \cdot {V tail}^{2} \cdot S t}

CT_lift - Tail Lift Coefficient?M_t - Pitching Moment due to Tail?𝒍_t - Horizontal Tail Moment Arm?ρ_∞ - Freestream Density?V_tail - Velocity Tail?S_t - Horizontal Tail Area?

Tail Lift Coefficient for given Pitching Moment Example

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

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

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

0.3 = - 2 \cdot \frac{-218.6644}{0.8015 \cdot 1.225 \cdot {28.72}^{2} \cdot 1.8}

0.3 = - 2 \cdot \frac{-218.6644N*m}{0.8015m \cdot 1.225kg/m³ \cdot {28.72m/s}^{2} \cdot 1.8m²}

0.3 = - 2 \cdot \frac{-218.6644}{0.8015 \cdot 1.225 \cdot {28.72}^{2} \cdot 1.8}

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Tail Lift Coefficient for given Pitching Moment Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

CT lift = - 2 \cdot \frac{-218.6644N*m}{0.8015m \cdot 1.225kg/m³ \cdot {28.72m/s}^{2} \cdot 1.8m²}

Next Step Prepare to Evaluate

∴

CT lift = - 2 \cdot \frac{-218.6644}{0.8015 \cdot 1.225 \cdot {28.72}^{2} \cdot 1.8}

Next Step Evaluate

∴

CT lift = 0.299999911426611

LAST Step Rounding Answer

∴

CT lift = 0.3

Tail Lift Coefficient for given Pitching Moment 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

Pitching Moment due to Tail

Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.

Symbol: M_t

Measurement: Moment of ForceUnit: N*m

Note: Value can be positive or negative.

Formulas to find Pitching Moment due to Tail

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

Freestream Density

Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.

Symbol: ρ_∞

Measurement: DensityUnit: kg/m³

Note: Value can be positive or negative.

Formulas to find Freestream Density

Velocity Tail

Velocity Tail refers to the airspeed or velocity of the horizontal stabilizer (tail) of an aircraft relative to the surrounding air (relative wind).

Symbol: V_tail

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Velocity Tail

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 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 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 for given Pitching Moment?

Tail Lift Coefficient for given Pitching Moment evaluator uses Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^2*Horizontal Tail Area) to evaluate the Tail Lift Coefficient, Tail Lift Coefficient for given Pitching Moment is a dimensionless quantity that characterizes the rotating motion of the horizontal tail, influenced by the pitching moment, horizontal tail moment arm, freestream density, tail velocity, and horizontal tail area, enabling the calculation of the tail's lift force in aerodynamic systems. Tail Lift Coefficient is denoted by CT_lift symbol.

How to evaluate Tail Lift Coefficient for given Pitching Moment using this online evaluator? To use this online evaluator for Tail Lift Coefficient for given Pitching Moment, enter Pitching Moment due to Tail (M_t), Horizontal Tail Moment Arm (𝒍_t), Freestream Density (ρ_∞), Velocity Tail (V_tail) & Horizontal Tail Area (S_t) and hit the calculate button.

FAQs on Tail Lift Coefficient for given Pitching Moment

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

The formula of Tail Lift Coefficient for given Pitching Moment is expressed as Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^2*Horizontal Tail Area). Here is an example- 0.3 = -2*(-218.6644)/(0.801511*1.225*28.72^2*1.8).

How to calculate Tail Lift Coefficient for given Pitching Moment?

With Pitching Moment due to Tail (M_t), Horizontal Tail Moment Arm (𝒍_t), Freestream Density (ρ_∞), Velocity Tail (V_tail) & Horizontal Tail Area (S_t) we can find Tail Lift Coefficient for given Pitching Moment using the formula - Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^2*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=Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*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 for given Pitching Moment Formula

​GoTail Lift Coefficient of Wing-Tail Combination Formula

​GoTail Lift Coefficient for given Pitching Moment Coefficient Formula

Tail Lift Coefficient for given Pitching Moment Example

Tail Lift Coefficient for given Pitching Moment Solution

Tail Lift Coefficient for given Pitching Moment 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?

FAQs on Tail Lift Coefficient for given Pitching Moment

Variable Name

GoTail Lift Coefficient of Wing-Tail Combination Formula

GoTail Lift Coefficient for given Pitching Moment Coefficient Formula