Flow over an airfoil

                                       Flow over naca air foil

Introduction: this assignment is about calculating the drag force and lift force acting on an air foil with different angle of attack this assignment gave me an insight of how to set up an air foils shaped structures into solid work domain.this assignment helped me better understand the user interface in the calculation .this tool can be used to back result data for various types of flow related problem.

Explanation:

• insert the airfoil profile into the solid works and convert it into a sketch
• then move the sketch to a particular angle as required with the x-axis or the flow direction
• then open up the flow simulation wizard enter all the preliminary conditions (flow velocity x-axis:25m/s,gas:air)
• this is a time dependent simulation with a duration of 5sec with 1sec interval
• the wizard setup is done after that, we have to extend the computation domain to a suitable size so that it mimics a real life condition
• set the computation as 2d simulation, set up the global mesh and local mesh which refines the mesh at the face of the air foils which is very much-needed
• the goals are set so that calculation can be performed on that
• hit run to calculate the data
• we wait until the goal values are been stabilized to a particular value after n-iterations 
• then we compare the  all the drag and lift forces for all the lift angles 

results:

0degree tilt

2degree tilt

4degree tilt

6degree tilt

8dergree

10degee of tilt

the results of these plots shows us that as the angle of attack increases 

the drag force (sgforce(x))

and the lift force (sgforce(y)) increases this due to the change in the frontal area exposed to the flowing air.