Speeds of of 80 to 120 mph were used to represent medium-high vehicle speeds. The AOA values were increased by in increments of 5 degrees, with additional data taken at AOA values of 12 and 13 degrees (the reason for this will be discussed in a bit). Downforce (or "negative lift") and drag values are recorded for each configuration. Data values gathered from 18 different configurations were recorded using a combination 6 AOA values (0, 5, 10, 12, 13, and 15 degrees) and 3 free-stream air speeds (80, 100, and 120 mph). A ruler that is placed on top of the center section of the GTC-series airfoil would be the real-life equivalent of this reference line.ĬFD simulations were conducted on a range of AOA values from 0 to 15 degrees, and speeds of 80 to 165 mph. For the CFD simulations conducted on the GTC-series airfoils, the center cross-section of the reference plane (or "center reference line") is used in place of the "chord line." Therefore, the AOA is defined herein as the difference in angle between the center cross-section of the reference plane (shown in the image below) and the vector that represents the relative motion of the undisturbed free-stream air flow. Typically, the AOA is defined as the difference in angle between the chord line and the vector that represents the undisturbed free-stream air flow, where the chord line is the line that passes from the leading edge to the trailing edge of the center section of the airfoil. Additionally, the analysis contained herein will provide insight with regards to how to apply this data to real world applications.
This data will provide insight with regards to how the airfoil performs with respect to these conditions. This data illustrates how the airfoil performs in free-stream air flow by comparing Downforce vs. CONNECTING THE DATA TO REAL-WORLD APPLICATIONĬontained herein are the data and results of the Computational Fluid Dynamics (CFD) analysis that was conducted on the a 3D model of the GTC-300 airfoil.
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