Lift due to Wing only Calculator

✖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 Force [F_L]			+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%

✖Lift due to Wing is the lift force acting on the wing (only) of an aircraft.ⓘ Lift due to Wing only [L_w]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Wing Tail Contribution Formulas PDF PDF Image

Lift due to Wing only Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Lift due to Wing - (Measured in Newton) - Lift due to Wing is the lift force acting on the wing (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 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 Force: 1073.04 Newton --> 1073.04 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

L_w = F_L-L_t --> 1073.04-273.04

Evaluating ... ...

L_w = 800

STEP 3: Convert Result to Output's Unit

800 Newton --> No Conversion Required

FINAL ANSWER

800 Newton <-- Lift due to Wing

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Wing Tail Contribution » Lift due to Wing only

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

Lift due to Wing only Formula

LaTeX Go

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

What generates most of an airplane's lift?

Every part of the airplane generates lift, but most of the lift on a normal airliner is generated by the wings.

How to Calculate Lift due to Wing only?

Lift due to Wing only calculator uses Lift due to Wing = Lift Force-Lift due to Tail to calculate the Lift due to Wing, Lift due to Wing only is a measure of the upward force exerted on an aircraft's wing, calculated by subtracting the lift force of the tail from the overall lift force, providing insight into the wing's contribution to the airplane's overall lift and stability. Lift due to Wing is denoted by L_w symbol.

How to calculate Lift due to Wing only using this online calculator? To use this online calculator for Lift due to Wing only, enter Lift Force (F_L) & Lift due to Tail (L_t) and hit the calculate button. Here is how the Lift due to Wing only calculation can be explained with given input values -> -249.04 = 1073.04-273.04.

FAQ

What is Lift due to Wing only?

Lift due to Wing only is a measure of the upward force exerted on an aircraft's wing, calculated by subtracting the lift force of the tail from the overall lift force, providing insight into the wing's contribution to the airplane's overall lift and stability and is represented as L_w = F_L-L_t or Lift due to Wing = Lift Force-Lift due to Tail. 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 Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft.

How to calculate Lift due to Wing only?

Lift due to Wing only is a measure of the upward force exerted on an aircraft's wing, calculated by subtracting the lift force of the tail from the overall lift force, providing insight into the wing's contribution to the airplane's overall lift and stability is calculated using Lift due to Wing = Lift Force-Lift due to Tail. To calculate Lift due to Wing only, you need Lift Force (F_L) & Lift due to Tail (L_t). With our tool, you need to enter the respective value for Lift Force & 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.

Home

FREE PDFs

🔍 Search