Challenge

Flow over an airfoil

Aim :- To model the flow over a NACA0017 airfoil for the given angle of attacks and to compare the lift and drag forces

Objective :-

To model the flow over a NACA0017 airfoil for the angle of attacks 0,2,4,6,8,10,etc.
To compare the lift and drag force for each case

Theory :-

An airfoil or aerofoil is the cross-sectional shape of a wing, blade (of a propeller, rotor, or turbine), or sail
An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag.
airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces.
The lift on an airfoil is primarily the result of its angle of attack. When oriented at a suitable angle, the airfoil deflects the oncoming air (for fixed-wing aircraft, a downward force), resulting in a force on the airfoil in the direction opposite to the deflection. This force is known as aerodynamic force and can be resolved into two components: lift and drag.

Design / Part :-

The Naca_0017_Airfoil is shown below having the angle of attack 0,2,4,6,8 & 10

Flow Analysis :-

For Case-2 , 2 degree angle of attack
The surface plot i.e. the drag & lift forces plots are shown below
The cutplot for this case is shown below (due to less iterations travelled the flow area is less )

For Case-3 , 4 degree angle of attack :-
The surface plot i.e. the drag & lift forces plots are shown below
The cutplot for this case is shown below ( as the more iterations travelled the flow area also increases )

For Case-5 , 8 degree angle of attack
The surface plot i.e. the drag & lift forces plots are shown below
The cutplot for this case is shown below ( the more flow seems to be flowing below the surface of the air foil )

For Case-6 , 10 degree angle of attack
The surface plot i.e. the drag & lift forces plots are shown below ( the graph shows a smooth line )
The cutplot for this case is shown below ( as the angle of attack increases the flow below the lower surface of the foil seems to be increasing )

Explanation :-

Software used solid works 2016
Using the data for the NACA_0017_AirFoil & the air foil curve is generated then extruding it to a specific length and then to apply different angle of attack to the airfoil
Now as we want the flow Outside the airfoil so set new flow simulation
Time analysis used is 5 sec for the total analysis time and 1 sec for end time
Air Flow is used under this case
Considering the velocity as 600m/s and running the baseline simulation to find out the flow in X direction
Setting up the Global goal for the forces & frictional forces along the X & Y direction
Also setting up Surface goal for X & Y same as shown in video.
Now Running the study and wait for the calculations been done for the iterations once its done we can obtain the cutplot
Thus the values for the lift and drag forces are calculated and graph is obtained.

The Graphs for the

Are shown below