Flow over an airfoil
Aim
Aim of this challenge is to model the flow over a NACA0017 airfoil and to compare the results obtained for a different angle of attacks.
Introduction
In this challenge, we are been provided with the NACA airfoil database from which one of the specific airfoils is selected and the analysis is been made on it at different angles of attacks. And after which the lift and drag forces are calculated and compared.
Theory on the simulation
SOLIDWORKS Flow Simulation is an intuitive Computational Fluid Dynamics (CFD) solution embedded within SOLIDWORKS 3D CAD that enables you to quickly and easily simulate liquid and gas flow through and around your designs to calculate product performance and capabilities, this is the definition provided by Solidworks and to put it into simple words flow simulation is a tool that helps one to know the real-life flow values and also the path where and how one's fluid flows with given boundary condition so by which he can edit up to his wish and necessity.
Case setup
In this case setup, there are two main steps one is the modeling of the airfoil, and the second id setting up the computational domain and running up the simulation and calculating the results.
Modeling
In this modeling phase, the airfoils model is inserted from the airfoil database and edited in such a way that Solidworks takes it up and its extruded to a random number dimension. With this our model is done and ready for simulation.
https://drive.google.com/drive/folders/1SvdKZMJeuc97Le8uoGDBJpfuSHJSR-Tp?usp=sharing
The above mentioned is the link for the part file and the result folders.
Flow setup
To start with we are using the wizard tool to make up the setup where firstly the projects name and the units are provided, then the flow is chosen as an external flow and the time dependency is selected, then the fluid is selected as air, finally the velocity at a particular direction is given as an input. Then the computational domain is changed to 2D and the width and length of them are made larger enough. Then the global, surface plots are made in order to find the lift and drag forces. Now the setup is ready for simulation.
CASE - 1 Angle of Attack 0
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
The values are provided below where the lift is very low at 0 angles of attack.
Plots and the contours
CASE - 2 Angle of Attack 2
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
Plots and the contours
CASE - 3 Angle of Attack 4
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
Plots and the contours
CASE - 4 Angle of Attack 6
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
Plots and the contours
CASE - 5 Angle of Attack 8
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
Plots and the contours
CASE - 6 Angle of Attack 10
After hitting the RUN button we will be getting our results done and after which we are able o have the values of SG forces in both the X and Y direction which are termed as the drag and lift forces of this airfoil.
Plots and the contours
Observation and the conclusion
From the above simulation and the plots we can clearly see that the lift force and the drag force is depending on the angle of attack, that is there's a drastic change when we compare the forces at 0 angles of attack and the 10 angles of attack.
And also we are clearly able to note lift and drag forces dependency on each other.
comparison of the lift and drag forces
Comparison of lift and drag forces for the angle of attack is given below
ANGLE OF ATTACK - LIFT FORCE - DRAG FORCE
0 - 12.93 - 1344
2 - 699 - 1378
4 - 1988 - 1543
6 - 3929 - 2091
8 - 6925 - 3454
10 - 8711 - 5857
These above-mentioned values are the values obtained from the simulation results,
NOTE*
Since I am facing a problem while uploading folder in my name as specified by you, like RAHUL_Airfoil I am unable to attach the files in such name but I have created a folder as per your regarding and added up the files, please take this in to account.