Tail Lift for given Tail Pitching Moment Calculator

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Pitching Moment due to Tail [M_t]			+10% -10%
✖The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.ⓘ Horizontal Tail Moment Arm [𝒍_t]			+10% -10%

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

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Tail Lift for given Tail Pitching Moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm)
L_t = -(M_t/𝒍_t)
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.
Pitching Moment due to Tail - (Measured in Newton Meter) - Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.
Horizontal Tail Moment Arm - (Measured in Meter) - The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.

STEP 1: Convert Input(s) to Base Unit

Pitching Moment due to Tail: -218.6644 Newton Meter --> -218.6644 Newton Meter No Conversion Required
Horizontal Tail Moment Arm: 0.801511 Meter --> 0.801511 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L_t = -(M_t/𝒍_t) --> -((-218.6644)/0.801511)

Evaluating ... ...

L_t = 272.815220252748

STEP 3: Convert Result to Output's Unit

272.815220252748 Newton --> No Conversion Required

FINAL ANSWER

272.815220252748 ≈ 272.8152 Newton <-- Lift due to Tail

(Calculation completed in 00.004 seconds)

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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!

< Tail Contribution Calculators

Tail Pitching Moment for given Moment Coefficient

LaTeX Go Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean Aerodynamic Chord)/2

Tail Pitching Moment for given Lift Coefficient

LaTeX Go Pitching Moment due to Tail = -(Horizontal Tail Moment Arm*Tail Lift Coefficient*Freestream Density*Velocity Tail^2*Horizontal Tail Area)/2

Tail Lift for given Tail Pitching Moment

LaTeX Go Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm)

Pitching Moment due to Tail

LaTeX Go Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail

Tail Lift for given Tail Pitching Moment Formula

LaTeX Go

Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm)
L_t = -(M_t/𝒍_t)

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How to Calculate Tail Lift for given Tail Pitching Moment?

Tail Lift for given Tail Pitching Moment calculator uses Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm) to calculate 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 calculate Tail Lift for given Tail Pitching Moment using this online calculator? To use this online calculator 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. Here is how the Tail Lift for given Tail Pitching Moment calculation can be explained with given input values -> 272.8152 = -((-218.6644)/0.801511).

FAQ

What is Tail Lift for given Tail Pitching Moment?

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 and is represented as L_t = -(M_t/𝒍_t) or Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm). Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity & The Horizontal Tail Moment Arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.

How to calculate Tail Lift for given Tail Pitching Moment?

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 is calculated using Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm). To calculate Tail Lift for given Tail Pitching Moment, you need Pitching Moment due to Tail (M_t) & Horizontal Tail Moment Arm (𝒍_t). With our tool, you need to enter the respective value for Pitching Moment due to Tail & Horizontal Tail Moment Arm 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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