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For my IB HL Physics IA, I have chosen to investigate the characteristics of NACA 2412 airfoils with a specific focus on the camber and thickness of airfoil cross sections and its relationship to the critical angle of attack, ideal flight, windspeed, and the lift-to-drag ratio (L/D). To conduct my investigation, I will be designing and 3D printing modified variations to the NACA 2412 airfoil. The airfoils will then be tested in a wind tunnel under controlled conditions, and I will collect data and conduct statistical analysis and graphing to draw conclusions. By conducting this experiment, I hope to gain a deeper understanding of the fundamental principles of airfoils and their applications in aeronautics.
Process & Learnings
Process & Learnings
• I started my investigation by researching and reading scientific papers on airfoil design and their characteristics. This involved studying databases such as ScienceDirect, JSTOR, and Google Scholar, as well as relevant textbooks on aeronautics. Links and Sources are below.
DESIGNING
After reviewing existing literature, I began designing the airfoils in Blender, an open-source 3D modeling software. I created a variety of designs with different chord lengths, thickness, Reynold;s Numbers, materials, etc. ensuring that each model would fit within the dimensions of the wind tunnel used in the experiment.
• Once I had finalized the designs, I used a school 3D printer to produce the airfoil models. This required setting up the printer with the correct specifications, materials, filling percents, etc. and ensuring that the printer was properly calibrated to produce accurate and precise prints.
3D NACA 2412 Airfoil Designs on Blender
Original NACA 2412
20% Thickness Increase
20% Thickness Reduction
20% Dimension Reduction
TESTING
• After printing the models, I conducted a series of tests in a wind tunnel to measure the lift and drag forces generated by each airfoil model. The wind tunnel was set up with precise measurements of wind speed, angle of attack, and other relevant parameters to ensure accurate results. Wind speed, the different designs, and windspeed were the independent variables.
• During testing, I recorded and analyzed data using various statistical tools and methods, including graphing and margin error. This allowed me to determine any trends or relationships between the chord length and the lift-to-drag ratio, critical angle of attack, and other flight parameters.
• After completing the testing and data analysis, I presented my findings and conclusions in a detailed report, which included all relevant data, graphs, and statistical analysis. I also included a discussion of the limitations of the experiment and suggestions for future research.
Overall, the experiment required careful planning, attention to detail, and a thorough understanding of the fundamental principles of aeronautics.
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