Flow over an airfoil

Aim : Model the flow over a NACA0017 Airfoil for the angle of attack 0,2,4,6,8,10 Compare the lift anddrag force.

Introduction : The NACA Airfoil are Airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA". The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.

In my case according to create project in NACA0017 Airfoil which data file is download from official website of airfoiltools.com

Procedure :

1.) first to import data file in solidwork and convert in to entity.

2.) adjust angle for requirement from 0 to 10 degree and the convert in to solid part.

3.) create wizard for external simulation and use time dependent.

4.) use air as fluid flow 600 m/s in x direction.

5.) remain use default .

6.) convert computational domain in 2D and adjust according to flow.

7.) use global goal (Normal force in (X) and (Y)) direction and friction force in (x) and (y) direction.

8.) also use surface goal for friction forces in (x) and (y) direction.

9.) use basic and local mesh in the surface.

10.) and the RUN the program.

11.) after completion calculation over result is obtained in result column.

12.) add cut plot for velocity and arrange colour bar for 200 shades of colour.

13.) now we have obtained simulation result for lift and drag force with different colour range.

RESULTS

Angle of Attack	drag force	Lift force
0	159.888	1.235

For velocity

For pressure :

Angle of Attack	drag force	Lift force
2	178.832	385.015

For velocity :

For pressure :

Angle of Attack	drag force	Lift force
4	191.251	732.586

For velocity :

for Pressure :

Angle of Attack	drag force	Lift force
6	302.559	1132.589

For velocity :

for pressure :

Angle of Attack	drag force	Lift force
8	351.416	1494.231

For velocity :

for pressure :

Angle of Attack	drag force	Lift force
10	532.071	1757.258

For velocity :

for pressure :

this are the resultsd which will obtained from 0 to 10 degree simulation and also obtained average drag force and average lift force force.

Angle of Attack	drag force	Lift force
0	159.888	1.235
2	178.832	385.015
4	191.251	732.586
6	302.559	1132.589
8	351.416	1494.231
10	532.071	1757.258

Pot graph between drage force vs angle of attack

Pot graph between Lift force vs angle of attack

Pot graph between drage force vs lift force

Conclusions:

With the help of SOLIDWORKS Flow Simulation, successful analysis of the NACA-0017 airfoil has been carried at various angles of attack (0, 2, 4, 6, 8, 10 degrees) and following observation has been made.

• With the increase in angle of attack, the number of iterations required to give the result get reduced.
• With the increase in angle of attack, Drag force increases slowly and lift force increases rapidly.
• With the increase in angle of attack, the velocity of air over the airfoil increased