Flow over an airfoil

Flow over an Air foil using solidworks. 

Aim

To perform an external flow simulation on a NACA 0017 airfoil and compare the drag and lift force for every angle of attack at 0,2,4,6,8and10 deg.

Objective

1.Download the NACA0017 file from the airfoil database and insert it into the solidworks curves with proper coordinate text to Model the curve.

2.Perform the simulation and analyse the drag and lift force for every angle of attack from 0 to 10 degree with interval of 2

3.Compare the different cases of plots of Velocity and pressure

Introduction:

 

NACA stands for National Advisory Committee for Aeronautics. The NACA airfoils are used to design aircraft wings, which consists of a series of numbers.

in which:

1.The first digit describes maximum camber as a percentage of chord.

2.The second digit describes the distance of maximum camber from airfoil leading edge intents of chord.

3.The last two digits gives the maximum thickness of the airfoil as percent of chord.

diagram of a airofoil:

Parameters:

Flow Simulation External

Pressure = 101325 Pa

Temperature = 293.2 K

Velocity along x-axis =600 m/s

Medium = Air

Time dependent study

Steps:

1.Insert the NACA airfoil .txt file from the airfoil database provided.

2.Sketch the airfoil by connecting the ends and Extrude. 

3.Activate the flow simulation and add the parameters. 

4.Select 2D computational domain . 

5.Edit the global mesh into fine mesh and local mesh

at the face of the curve for refinement.

6.Set surface goals to calculate the drag and lift force. 

7.simulate for various angle of attack ranging from 0 to 10.

RESULTS:

Here the SG(X) represents the drag force. 

Here the SG(Y) represents the lift force. 

 PLOT AT ZERO DEGREE ATTACK. 

Velocity plot at 0 degree angle of attack

pressure plot:

OBSERVATION:

drag force :0.002 N

lift:-4.327e-006 N

PLOT AT 2 DEGREE ANGLE OF ATTACK

Velocity plot:

pressure plot:

OBSERVATION:

drag force : 1.952e-004 N

lift: -5.729e-006 N

PLOT AT 4 DEGREE ANGLE OF ATTACK

velocity plot

pressure plot:

OBSERVATION:

drag force : 0.002N

lift: 0.001N

PLOT FOR 6 DEGREE ANGLE OF ATTACK:

Velocity plot 

pressure plot:

OBSERVATION:

drag force : 1.875e-004 N

lift: -1.471e-005 N

PLOT FOR 8 DEGREE ANGLE OF ATTACK:

Velocity plot 

pressure plot:

OBSERVATION:

drag force :0.002N

lift: 0.003

 OBSERVATION FOR 10 DEGREE ANGLE OF ATTACK

drag force :0.002N

lift: 0.003N

CONCLUSION:

1.At zero degree angle of attack the lift is found to be zero due to symmetry of airfoil.

2.there is symmetry found in velocity and pressure plot at 0 deg angle of attack.

3.As the angle of attack increses from 0 to 10 the lift force also increases.

4.due to this size of wake region also increases.

5.The blue light increses below the airfoil in the pressure plot as angle of attack is increased as pressure increases in that region.

6.Similarly as the velocity flows over the airfoil more than the lower region the pressure under it decreases this creates suction and causes lift.