Airfoil(NACA0017) flow analysis in solidwork

OBJECTIVE

Here we will perform a flow analysis on NACA0017 airfoil with different angle of attack and compare the result of drag force and lift force for each case

to model the airfoil we need x,y,z points in solidwork and link to this file can be found in link given below

http://airfoiltools.com/airfoil/naca4digit

PROCEDURE

-First of all we will model the airfoil in solidwok using curve and we will browse for file and insert it and then we conver entites and close the curve and extrude it in solidwork we will use MKS unit system while modeling the airfoil

-then we will perform flow analysis on this and look for the surface goal in x and y direction

here x direction force gives the drag force and y direction force gives the lift force. These goals are surface goal denoted by SG Force (X) and SG Force (Y)

-we will vary angle of attack for 0 , 2 , 4 , 6 , 8 , 10 degrees and see results for each case

-air velocity in x direction is 600m/s and physicas time is 0.02 sec

-we will set global mesh at 2 and local mesh at the surface of the airfoil at 3 which is shown below

RESULTS

-Angle of attack 0 degree

pressure plot

velocity plot

forces

-Angle of attack 2 degree

pressure plot

velocity plot

forces

-Angle of attack 4 degree

pressure plot

velocity plot

forces

-Angle of attack 6 degree

pressure plot

velocity plot

forces

-Angle of attack 8 degree

pressure plot

velocity plot

forces

-Angle of attack 10 degree

pressure plot

velocity plot

forces

Now we will compare the result in form of graph so that we can see the difference in each case

-drag force vs angle of attack

Here from the graph we can see that the drag force is increasing gradually like exponential for the angle of attack between 0 to 10 degree

-lift force vs angle of attack

here we can see that lift force is increasing linearly with increase in the angle of attack