Lift due to Tail only Calculator

✖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.ⓘ Lift Force [F_L]			+10% -10%
✖Lift due to Wing is the lift force acting on the wing (only) of an aircraft.ⓘ Lift due to Wing [L_w]			+10% -10%

✖Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.ⓘ Lift due to Tail only [L_t]

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Lift due to Tail only Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift due to Tail = Lift Force-Lift due to Wing
L_t = F_L-L_w
This formula uses 3 Variables

Variables Used

Lift due to Tail - (Measured in Newton) - Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.
Lift Force - (Measured in Newton) - 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.
Lift due to Wing - (Measured in Newton) - Lift due to Wing is the lift force acting on the wing (only) of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Lift Force: 1073.04 Newton --> 1073.04 Newton No Conversion Required
Lift due to Wing: 800 Newton --> 800 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L_t = F_L-L_w --> 1073.04-800

Evaluating ... ...

L_t = 273.04

STEP 3: Convert Result to Output's Unit

273.04 Newton --> No Conversion Required

FINAL ANSWER

273.04 Newton <-- Lift due to Tail

(Calculation completed in 00.004 seconds)

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Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< Wing Tail Contribution Calculators

Angle of incidence of wing

LaTeX Go Wing Incidence Angle = Wing Angle of Attack-Horizontal Tail Angle of Attack-Downwash Angle+Tail Incidence Angle

Angle of Attack at Tail

LaTeX Go Horizontal Tail Angle of Attack = Wing Angle of Attack-Wing Incidence Angle-Downwash Angle+Tail Incidence Angle

Angle of Attack of Wing

LaTeX Go Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle

Downwash angle

LaTeX Go Downwash Angle = Wing Angle of Attack-Wing Incidence Angle-Horizontal Tail Angle of Attack+Tail Incidence Angle

Lift due to Tail only Formula

LaTeX Go

Lift due to Tail = Lift Force-Lift due to Wing
L_t = F_L-L_w

What is cantilever wing?

A wing that uses no external struts or bracing is a cantilever wing. All support is obtained from the wing itself. The wing spars are built in such a way that they carry all the torsion and bending loads.

How to Calculate Lift due to Tail only?

Lift due to Tail only calculator uses Lift due to Tail = Lift Force-Lift due to Wing to calculate 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 L_t symbol.

How to calculate Lift due to Tail only using this online calculator? To use this online calculator for Lift due to Tail only, enter Lift Force (F_L) & Lift due to Wing (L_w) and hit the calculate button. Here is how the Lift due to Tail only calculation can be explained with given input values -> -776 = 1073.04-800.

FAQ

What is Lift due to Tail only?

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 and is represented as L_t = F_L-L_w or Lift due to Tail = Lift Force-Lift due to Wing. 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 & Lift due to Wing is the lift force acting on the wing (only) of an aircraft.

How to calculate Lift due to Tail only?

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 is calculated using Lift due to Tail = Lift Force-Lift due to Wing. To calculate Lift due to Tail only, you need Lift Force (F_L) & Lift due to Wing (L_w). With our tool, you need to enter the respective value for Lift Force & Lift due to Wing and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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