## 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 - Trigonometric sine function, sin(Angle)
cos - Trigonometric cosine function, 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
8.10948673695653 Newton <-- Lift on Airfoil
(Calculation completed in 00.018 seconds)
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## Credits

Created by Vishal Anand
Indian Institute of Technology Kharagpur (IIT KGP), Kharagpur
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Gautam Buddha University (GBU), Greater Noida
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## < 7 CFD- Computational Fluid Dyanmics Calculators

Drag on airfoil
Drag on Airfoil = Normal Force on Airfoil*sin(Angle of Attack of Airfoil)+Axial Force on airfoil*cos(Angle of Attack of Airfoil) Go
Lift on airfoil
Lift on Airfoil = Normal Force on Airfoil*cos(Angle of Attack of Airfoil)-Axial Force on airfoil*sin(Angle of Attack of Airfoil) Go
Reynolds Number for airfoil
Reynolds Number = (Density of Fluid*Flow Velocity*Chord Length of Airfoil)/Dynamic Viscosity Go
Y plus
Y Plus = First layer height*Density of air*Friction Velocity for Airfoil/Kinematic viscosity Go
Wall Shear Stress for airfoil
Wall Shear Stress for Airfoil = 0.5*Skin friction coefficient*Flow Velocity*Density of air Go
Friction Velocity for airfoil
Friction Velocity for Airfoil = (Wall Shear Stress for Airfoil/Density of air)^0.5 Go
Skin friction coefficient
Skin friction coefficient = (2*log10(Reynolds Number)-0.65)^(-2.30) Go

## Lift on airfoil Formula

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 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 formula is defined as the component of the resultant force acting on an airfoil in the direction perpendicular to freestream velocity. 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 formula is defined as the component of the resultant force acting on an airfoil in the direction perpendicular to freestream velocity 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 formula is defined as the component of the resultant force acting on an airfoil in the direction perpendicular to freestream velocity 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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