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
Lt = -Mt/𝒍t
This formula uses 3 Variables
Variables Used
Lift due to tail - (Measured in Newton) - Lift due to tail is the lift force acting on the tail (only) 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: -218.43 Newton Meter --> -218.43 Newton Meter No Conversion Required
Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Lt = -Mt/𝒍t --> -(-218.43)/0.8
Evaluating ... ...
Lt = 273.0375
STEP 3: Convert Result to Output's Unit
273.0375 Newton --> No Conversion Required
FINAL ANSWER
273.0375 Newton <-- Lift due to tail
(Calculation completed in 00.004 seconds)

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!

19 Tail Contribution Calculators

Tail Pitching moment coefficient for given tail efficiency
Go Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)
Tail Efficiency for given pitching moment coefficient
Go Tail Efficiency = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient)
Tail moment arm for given tail moment coefficient
Go Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
Tail area for given tail moment coefficient
Go Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
Mean aerodynamic chord for given tail pitching moment coefficient
Go Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)
Tail Pitching moment coefficient
Go Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)
Tail Pitching moment for given moment coefficient
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
Go Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2
Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio)
Wing Reference area for given horizontal tail volume ratio
Go Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)
Horizontal tail volume ratio
Go Horizontal Tail Volume Ratio = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)
Tail moment arm for given horizontal tail volume ratio
Go Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
Horizontal tail area for given tail volume ratio
Go Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
Horizontal tail volume ratio for given pitching moment coefficient
Go Horizontal Tail Volume Ratio = -Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient)
Tail lift coefficient for given tail volume ratio
Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
Tail Efficiency for given tail volume ratio
Go Tail Efficiency = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Lift Coefficient)
Tail Pitching moment coefficient for given tail volume ratio
Go Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient
Tail lift for given tail pitching moment
Go Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm
Pitching moment due to tail
Go Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail

Tail lift for given tail pitching moment Formula

Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm
Lt = -Mt/𝒍t

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In aeronautics and aeronautical engineering, camber is the asymmetry between the two acting surfaces of an airfoil, with the top surface of a wing (or correspondingly the front surface of a propeller blade) commonly being more convex (positive camber). An airfoil that is not cambered is called a symmetric airfoil.

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, The Tail lift for given tail pitching moment is a function of the pitching moment due to the tail and the moment arm (distance between tail lift center and center of gravity of aircraft). Lift due to tail is denoted by Lt 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 (Mt) & Horizontal tail moment arm (𝒍t) and hit the calculate button. Here is how the Tail lift for given tail pitching moment calculation can be explained with given input values -> 273.0375 = -(-218.43)/0.8.

FAQ

What is Tail lift for given tail pitching moment?
The Tail lift for given tail pitching moment is a function of the pitching moment due to the tail and the moment arm (distance between tail lift center and center of gravity of aircraft) and is represented as Lt = -Mt/𝒍t 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?
The Tail lift for given tail pitching moment is a function of the pitching moment due to the tail and the moment arm (distance between tail lift center and center of gravity of aircraft) 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 (Mt) & Horizontal tail moment arm (𝒍t). 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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