Total Lift of wing-tail combination Calculator

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Static Stability and Control

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Longitudinal Stability

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Directional Stability

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Longitudinal Control

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Wing-Tail Contribution

Fuselage Contribution

Tail Contribution

✖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 is the lift force acting on the tail (only) 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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Formula

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Total Lift of wing-tail combination

Formula

`"F"_{"L"} = "L"_{"w"}+"L"_{"t"}`

Example

`"1073.04N"="800N"+"273.04N"`

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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 is the lift force acting on the tail (only) 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 00.004 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!

< 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

Total Lift of wing-tail combination Formula

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, The Total Lift of wing-tail combination is the sum of the lift generated by wing and tail alone for a given aircraft. 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?

The Total Lift of wing-tail combination is the sum of the lift generated by wing and tail alone for a given aircraft 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 is the lift force acting on the tail (only) of an aircraft.

How to calculate Total Lift of wing-tail combination?

The Total Lift of wing-tail combination is the sum of the lift generated by wing and tail alone for a given aircraft 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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