FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Tail Lift for given Tail Pitching Moment Formula

Fx Copy

LaTeX Copy

Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft. Check FAQs

L t = - (\frac{M t}{𝒍 t})

L_t - Lift due to Tail?M_t - Pitching Moment due to Tail?𝒍_t - Horizontal Tail Moment Arm?

Tail Lift for given Tail Pitching Moment Example

With values

With units

Only example

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

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

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

272.8152 = - (\frac{-218.6644}{0.8015})

272.8152N = - (\frac{-218.6644N*m}{0.8015m})

272.8152 = - (\frac{-218.6644}{0.8015})

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aircraft Mechanics » fx Tail Lift for given Tail Pitching Moment

Tail Lift for given Tail Pitching Moment Solution

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

FIRST Step Consider the formula

L t = - (\frac{M t}{𝒍 t})

Next Step Substitute values of Variables

∴

L t = - (\frac{-218.6644N*m}{0.8015m})

Next Step Prepare to Evaluate

∴

L t = - (\frac{-218.6644}{0.8015})

Next Step Evaluate

∴

L t = 272.815220252748N

LAST Step Rounding Answer

∴

L t = 272.8152N

Tail Lift for given Tail Pitching Moment Formula Elements

Variables

Lift due to Tail

Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

Symbol: L_t

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Lift due to Tail

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

Other formulas in Tail Contribution category

Go Tail Pitching Moment for given Lift Coefficient

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

Go Pitching Moment due to Tail

M t = - 𝒍 t \cdot L t

Go Tail Pitching Moment for given Moment Coefficient

M t = \frac{Cm t \cdot ρ ∞ \cdot V^{2} \cdot S \cdot c ma}{2}

Go Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient

c ma = \frac{M t}{0.5 \cdot ρ ∞ \cdot V^{2} \cdot S \cdot Cm t}

How to Evaluate Tail Lift for given Tail Pitching Moment?

Tail Lift for given Tail Pitching Moment evaluator uses Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm) to evaluate the Lift due to Tail, Tail Lift for given Tail Pitching Moment is a measure of the upward force exerted by the tailplane to counteract the rotation around the horizontal axis caused by the pitching moment, enabling the aircraft to maintain stability and control during flight. Lift due to Tail is denoted by L_t symbol.

How to evaluate Tail Lift for given Tail Pitching Moment using this online evaluator? To use this online evaluator for Tail Lift for given Tail Pitching Moment, enter Pitching Moment due to Tail (M_t) & Horizontal Tail Moment Arm (𝒍_t) and hit the calculate button.

FAQs on Tail Lift for given Tail Pitching Moment

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

The formula of Tail Lift for given Tail Pitching Moment is expressed as Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm). Here is an example- 272.8152 = -((-218.6644)/0.801511).

How to calculate Tail Lift for given Tail Pitching Moment?

With Pitching Moment due to Tail (M_t) & Horizontal Tail Moment Arm (𝒍_t) we can find Tail Lift for given Tail Pitching Moment using the formula - Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm).

Can the Tail Lift for given Tail Pitching Moment be negative?

Yes, the Tail Lift for given Tail Pitching Moment, measured in Force can be negative.

Which unit is used to measure Tail Lift for given Tail Pitching Moment?

Tail Lift for given Tail Pitching Moment is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Tail Lift for given Tail Pitching Moment can be measured.

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Tail Lift for given Tail Pitching Moment Formula

Tail Lift for given Tail Pitching Moment Example

Tail Lift for given Tail Pitching Moment Solution

Tail Lift for given Tail Pitching Moment Formula Elements

Other formulas in Tail Contribution category

How to Evaluate Tail Lift for given Tail Pitching Moment?

FAQs on Tail Lift for given Tail Pitching Moment

Variable Name