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Airfoil Analysis

Considering air flowing over my NACA 1408 airfoil, with a constant flight speed of:

Re = 6*10^6

Assuming SSL values for the free stream properties:

Pressure = SSL (1 atm)

Density = SSL (1.225 [kg*m^-3])

Temperature = SSL (293.15 K)

Kinematic Viscosity = SSL (14.88*10^-6)

Chord Length = 1m

Velocity = Re*Kinematic Viscosity / Chord length = ((6*10^6) * (14.88*10^-6)) / 1m = 89.28 m/s

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After Generating the coordinates for the airfoil through a MATLAB code,  I was then able to import them as a geometry in COMSOL using an interpolated curve, the result is thus:

NACA 1408 Geometry with Dimensions:

Here is a close up of the Leading Edge (LE):

Here is a close up of the Trailing Edge (TE):

To begin:

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  • After importing the coordinates for the Airfoil Geometry, I placed a rectangular geometry around the Airfoil to simulate a wind tunnel

  • I used a normal mesh on the overall geometry of the airfoil as well as wind tunnel

  • I allowed for some Inlet and Outlet conditions 

Normal Mesh Consisting of 3,420 Triangular Elements

1st Study:

I used a flow of 1 m/s in the X and Y direction, the wall conditions were the left and bottom wall were the inlet, the top and right wall were the outlet:

  • These are the stats about the mesh in the 1st study

 

  • The Physics I utilized was a Turbulent flow Algebraic Plus, with 4 Stationary Studies with Initialization

 

  • I used standard atmospheric pressure of 1 atm

 

  • I used a standard reference temperature of 293.15 K

 

  • Later on, I used a Turbulent Flow SST

Velocity graph of 1 m/s, no angle of attack:

Pressure graph of 1 m/s, no angle of attack:

2nd Study:

For this study, I kept the same parameters however used a refined mesh denoted as (Finer) to gain more accurate values, and changed the flow velocity to fit our SSL flow properties as well as Re = 6*10^6

Inlet Variables

Mesh consisting of 140,000 Triangular Elements

Velocity with new parameters and refined mesh

Pressure with new parameters and refined mesh 

Difference in Pressure between 1st and 2nd Studies

3rd Study:

I used this study to calculate the pressure coefficient in the Top and Bottom curve

Pressure Coefficient for Bottom Curve

Pressure Coefficient for Top Curve

4th Study:

For this study I used the refined mesh, and conducted an analysis using the difference in values from the velocities and pressures from the previous studies

(Normal vs Finer Mesh) difference between both solutions

Join velocity with an altered range (-10-10)

Difference in Pressure between both Mesh studies

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