Flow Simulation using SolidWorks-Flow over an airfoil
Introduction
The aim of this challenge is to model the flow over a NACA0017 airfoil for the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces.
Procedure
The X,Y,Z plot points can be found out online from the given website.It is copied into the txt file in a certain format.It is put in the curves option in solidworks to plot the points.
The required angle of attach is setup in certain plane.
The curve is made a solid using the extrude option. This makes it an airfoil.
The flow simulation is setuup during which time the flow velocity as well as bounding box,goals,mesh etc are all setup.
The simulation is run and iterations are run until a solution is converged upon.
The values are recorded.
Results
Here the lift forces are along y axis and drag forces are along y axis.
Case 1: 0 Degree Angle of Attack.
Lift and Drag Forces
As expected there is negligible lift as the angle of attack is 0.
Pressure and Velocity
Case 2: 2 degree angle of Attack
Lift And Drag
Pressure And Velocity
Case 3: 4 degree Angle of Attack
Lift and Drag
Pressure and Velocity
Case 4:6 Degree angle of attack
Lift and Drag
Pressure and Velocity
Case 5: 8 Degrees Angle of Attack
Lift and Drag
Pressure and Velocity
Case 6: 10 Degree Angle of Attack
Lift and Drag Forces
Pressure and Velocity
Conclusions
1: The lift increases as the angle of attack increases. Ther is negligible lift at 0 degree angle of attack.
2:The drag increases as the angle of attack increases
3: The minimum pressure experienced by the airfoil decreases as the angle of attack increases. No obvious relation in the case of maximum pressure.
4: More high velocity air flows through the top of the airfoil as expected to generate required lift as the angle of attack increases.
5: Similiarly the low pressure region is also at the top of the airfoil as the angle of attack increases to generate the required lift.