Lift due to tail only Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift due to tail = Lift Force-Lift due to wing
Lt = FL-Lw
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.
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
Lt = FL-Lw --> 1073.04-800
Evaluating ... ...
Lt = 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)

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!

15 Wing-Tail Contribution Calculators

Tail lift coefficient for given pitching moment coefficient
Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm)
Tail lift coefficient for given pitching moment
Go Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area)
Tail Lift Coefficient of wing-tail combination
Go Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)
Tail Efficiency for given lift coefficients
Go Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal tail area)
Tail area for given tail efficiency
Go Horizontal tail area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
Total Lift Coefficient of wing-tail combination
Go Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
Wing Lift Coefficient of wing-tail combination
Go Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
Angle of incidence of wing
Go Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle
Angle of incidence of tail
Go Tail incidence angle = Horizontal tail angle of attack-Wing angle of attack+Wing incidence angle+Downwash angle
Angle of Attack at Tail
Go Horizontal tail angle of attack = Wing angle of attack-Wing incidence angle-Downwash angle+Tail incidence angle
Angle of attack of wing
Go Wing angle of attack = Horizontal tail angle of attack+Wing incidence angle+Downwash angle-Tail incidence angle
Downwash angle
Go Downwash angle = Wing angle of attack-Wing incidence angle-Horizontal tail angle of attack+Tail incidence angle
Total Lift of wing-tail combination
Go Lift Force = Lift due to wing+Lift due to tail
Lift due to wing only
Go Lift due to wing = Lift Force-Lift due to tail
Lift due to tail only
Go Lift due to tail = Lift Force-Lift due to wing

Lift due to tail only Formula

Lift due to tail = Lift Force-Lift due to wing
Lt = FL-Lw

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, The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone. Lift due to tail is denoted by Lt 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 (FL) & Lift due to wing (Lw) 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?
The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone and is represented as Lt = FL-Lw 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?
The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone is calculated using Lift due to tail = Lift Force-Lift due to wing. To calculate Lift due to tail only, you need Lift Force (FL) & Lift due to wing (Lw). 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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