Lift on Airfoil Calculator

✖Normal Force on Airfoil is component of resultant force acting on airfoil perpendicular to chord.ⓘ Normal Force on Airfoil [N]			+10% -10%
✖The Angle of Attack of Airfoil is the angle between freestream velocity and chord of the airfoil.ⓘ Angle of Attack of Airfoil [α^°]			+10% -10%
✖Axial Force on Airfoil is component of resultant force acting on airfoil parallel to chord.ⓘ Axial Force on Airfoil [A]			+10% -10%

✖Lift on Airfoil is component of resultant force acting on airfoil perpendicular to freestream Velocity.ⓘ Lift on Airfoil [L]

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Lift on Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil)
L = N*cos(α^°)-A*sin(α^°)
This formula uses 2 Functions, 4 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)
cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)

Variables Used

Lift on Airfoil - (Measured in Newton) - Lift on Airfoil is component of resultant force acting on airfoil perpendicular to freestream Velocity.
Normal Force on Airfoil - (Measured in Newton) - Normal Force on Airfoil is component of resultant force acting on airfoil perpendicular to chord.
Angle of Attack of Airfoil - (Measured in Radian) - The Angle of Attack of Airfoil is the angle between freestream velocity and chord of the airfoil.
Axial Force on Airfoil - (Measured in Newton) - Axial Force on Airfoil is component of resultant force acting on airfoil parallel to chord.

STEP 1: Convert Input(s) to Base Unit

Normal Force on Airfoil: 11 Newton --> 11 Newton No Conversion Required
Angle of Attack of Airfoil: 8 Degree --> 0.13962634015952 Radian (Check conversion here)
Axial Force on Airfoil: 20 Newton --> 20 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L = N*cos(α^°)-A*sin(α^°) --> 11*cos(0.13962634015952)-20*sin(0.13962634015952)

Evaluating ... ...

L = 8.10948673695653

STEP 3: Convert Result to Output's Unit

8.10948673695653 Newton --> No Conversion Required

FINAL ANSWER

8.10948673695653 ≈ 8.109487 Newton <-- Lift on Airfoil

(Calculation completed in 00.004 seconds)

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Credits

Created by Vishal Anand

Indian Institute of Technology Kharagpur (IIT KGP), Kharagpur

Vishal Anand has created this Calculator and 7 more calculators!

Verified by Ayush Singh

Gautam Buddha University (GBU), Greater Noida

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< Computational Fluid Dyanmics Calculators

Drag on Airfoil

LaTeX Go Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on Airfoil*cos(Angle of Attack of Airfoil)

Lift on Airfoil

LaTeX Go Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil)

Reynolds Number for Airfoil

LaTeX Go Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity

Friction Velocity for Airfoil

LaTeX Go Friction Velocity For Airfoil = (Wall Shear Stress For Airfoil/Density of Air)^0.5

Lift on Airfoil Formula

LaTeX Go

Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil)
L = N*cos(α^°)-A*sin(α^°)

How do airfoils generate lift?

An airfoil is the shape of an object that is designed to generate lift during its motion through air. A cross-section of an airplane wing has the shape of an airfoil. It generates lift by creating a pressure gradient between the air above and below the wing.

How to Calculate Lift on Airfoil?

Lift on Airfoil calculator uses Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil) to calculate the Lift on Airfoil, The Lift on Airfoil is the aerodynamic force that acts perpendicular to the direction of the airflow over the airfoil's surface. It is generated as a result of the pressure difference between the upper and lower surfaces of the airfoil. Lift is what enables an aircraft to generate upward force and stay aloft. Lift on Airfoil is denoted by L symbol.

How to calculate Lift on Airfoil using this online calculator? To use this online calculator for Lift on Airfoil, enter Normal Force on Airfoil (N), Angle of Attack of Airfoil (α^°) & Axial Force on Airfoil (A) and hit the calculate button. Here is how the Lift on Airfoil calculation can be explained with given input values -> 8.109487 = 11*cos(0.13962634015952)-20*sin(0.13962634015952).

FAQ

What is Lift on Airfoil?

The Lift on Airfoil is the aerodynamic force that acts perpendicular to the direction of the airflow over the airfoil's surface. It is generated as a result of the pressure difference between the upper and lower surfaces of the airfoil. Lift is what enables an aircraft to generate upward force and stay aloft and is represented as L = N*cos(α^°)-A*sin(α^°) or Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil). Normal Force on Airfoil is component of resultant force acting on airfoil perpendicular to chord, The Angle of Attack of Airfoil is the angle between freestream velocity and chord of the airfoil & Axial Force on Airfoil is component of resultant force acting on airfoil parallel to chord.

How to calculate Lift on Airfoil?

The Lift on Airfoil is the aerodynamic force that acts perpendicular to the direction of the airflow over the airfoil's surface. It is generated as a result of the pressure difference between the upper and lower surfaces of the airfoil. Lift is what enables an aircraft to generate upward force and stay aloft is calculated using Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on Airfoil*sin(Angle of Attack of Airfoil). To calculate Lift on Airfoil, you need Normal Force on Airfoil (N), Angle of Attack of Airfoil (α^°) & Axial Force on Airfoil (A). With our tool, you need to enter the respective value for Normal Force on Airfoil, Angle of Attack of Airfoil & Axial Force on Airfoil 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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