Total Lift of Wing-Tail Combination Calculator

✖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 [L_t]			+10% -10%

✖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.ⓘ Total Lift of Wing-Tail Combination [F_L]

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Total Lift of Wing-Tail Combination Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
Lift due to Tail - (Measured in Newton) - Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Lift due to Wing: 800 Newton --> 800 Newton No Conversion Required
Lift due to Tail: 273.04 Newton --> 273.04 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_L = L_w+L_t --> 800+273.04

Evaluating ... ...

F_L = 1073.04

STEP 3: Convert Result to Output's Unit

1073.04 Newton --> No Conversion Required

FINAL ANSWER

1073.04 Newton <-- Lift Force

(Calculation completed in 00.008 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

Total Lift of Wing-Tail Combination Formula

LaTeX Go

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

How do wings generate lift?

An airfoil generates lift by exerting a downward force on the air as it flows past. According to Newton's third law, the air must exert an equal and opposite (upward) force on the airfoil, which is lift.

How to Calculate Total Lift of Wing-Tail Combination?

Total Lift of Wing-Tail Combination calculator uses Lift Force = Lift due to Wing+Lift due to Tail to calculate the Lift Force, Total Lift of Wing-Tail Combination is a measurement of the combined upward force exerted by the wing and tail of an aircraft, influencing its stability and performance during flight, calculated by summing the individual lift forces generated by the wing and tail components. Lift Force is denoted by F_L symbol.

How to calculate Total Lift of Wing-Tail Combination using this online calculator? To use this online calculator for Total Lift of Wing-Tail Combination, enter Lift due to Wing (L_w) & Lift due to Tail (L_t) and hit the calculate button. Here is how the Total Lift of Wing-Tail Combination calculation can be explained with given input values -> 1073.04 = 800+273.04.

FAQ

What is Total Lift of Wing-Tail Combination?

Total Lift of Wing-Tail Combination is a measurement of the combined upward force exerted by the wing and tail of an aircraft, influencing its stability and performance during flight, calculated by summing the individual lift forces generated by the wing and tail components and is represented as F_L = L_w+L_t or Lift Force = Lift due to Wing+Lift due to Tail. Lift due to Wing is the lift force acting on the wing (only) of an aircraft & Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

How to calculate Total Lift of Wing-Tail Combination?

Total Lift of Wing-Tail Combination is a measurement of the combined upward force exerted by the wing and tail of an aircraft, influencing its stability and performance during flight, calculated by summing the individual lift forces generated by the wing and tail components is calculated using Lift Force = Lift due to Wing+Lift due to Tail. To calculate Total Lift of Wing-Tail Combination, you need Lift due to Wing (L_w) & Lift due to Tail (L_t). With our tool, you need to enter the respective value for Lift due to Wing & Lift due to Tail 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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