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Lift due to Tail only Formula

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Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft. Check FAQs
Lt=FL-Lw
Lt - Lift due to Tail?FL - Lift Force?Lw - Lift due to Wing?

Lift due to Tail only Example

With values
With units
Only example

Here is how the Lift due to Tail only equation looks like with Values.

Here is how the Lift due to Tail only equation looks like with Units.

Here is how the Lift due to Tail only equation looks like.

273.04Edit=1073.04Edit-800Edit
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Lift due to Tail only Solution

Follow our step by step solution on how to calculate Lift due to Tail only?

FIRST Step Consider the formula
Lt=FL-Lw
Next Step Substitute values of Variables
∴ Lt=1073.04N-800N
Next Step Prepare to Evaluate
∴ Lt=1073.04-800
LAST Step Evaluate
∴Lt=273.04N

Lift due to Tail only 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: Lt
Measurement: ForceUnit: N
Note: Value can be positive or negative.
Formulas to find Lift due to TailOpen Variable
Lift Force
The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.
Symbol: FL
Measurement: ForceUnit: N
Note: Value should be greater than 0.
Formulas to find Lift ForceOpen Variable
Lift due to Wing
Lift due to Wing is the lift force acting on the wing (only) of an aircraft.
Symbol: Lw
Measurement: ForceUnit: N
Note: Value can be positive or negative.
Formulas to find Lift due to WingOpen Variable

Other formulas in Wing Tail Contribution category

​Go Angle of Attack at Tail
αt=αw-𝒊w-ε+𝒊t
​Go Angle of Attack of Wing
αw=αt+𝒊w+ε-𝒊t
​Go Angle of incidence of wing
𝒊w=αw-αt-ε+𝒊t
​Go Downwash angle
ε=αw-𝒊w-αt+𝒊t

How to Evaluate Lift due to Tail only?

Lift due to Tail only evaluator uses Lift due to Tail = Lift Force-Lift due to Wing to evaluate the Lift due to Tail, Lift due to Tail only is a measure of the upward force exerted on an aircraft's tail section, calculated by subtracting the lift force of the wing from the total lift force, thereby providing a critical component in stabilizing the aircraft's longitudinal axis during flight. Lift due to Tail is denoted by Lt symbol.

How to evaluate Lift due to Tail only using this online evaluator? To use this online evaluator for Lift due to Tail only, enter Lift Force (FL) & Lift due to Wing (Lw) and hit the calculate button.

FAQs on Lift due to Tail only

What is the formula to find Lift due to Tail only?
The formula of Lift due to Tail only is expressed as Lift due to Tail = Lift Force-Lift due to Wing. Here is an example- -776 = 1073.04-800.
How to calculate Lift due to Tail only?
With Lift Force (FL) & Lift due to Wing (Lw) we can find Lift due to Tail only using the formula - Lift due to Tail = Lift Force-Lift due to Wing.
Can the Lift due to Tail only be negative?
Yes, the Lift due to Tail only, measured in Force can be negative.
Which unit is used to measure Lift due to Tail only?
Lift due to Tail only is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Lift due to Tail only can be measured.
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