This experiment focused on determining the lift coefficients and the pressure generated by a DU96 airfoil. These values ​​were determined using both an experimental setup in Virginia Tech's Stability Wind Tunnel and a computer model in a program called XFOIL. The XFOIL results will be used to compare the wind tunnel results to determine which parts of each are reasonable representations of what the airfoil would experience in open air. In the wind tunnel, the data will be corrected due to errors caused by the Kevlar sheets used to create more precise airflow and more accurate readings. The experiments were both carried out with a Reynolds number of two million and angles of attack ranging from minus sixteen to plus sixteen degrees. The corrected and uncorrected results were compared and it was determined that the corrected results were reasonable, but did not make a large difference in small changes in angle of attack. The airfoil was found to generate a lift coefficient of 1.49 in the computer model and 1.28 in the wind tunnel. Through these and other measurements, it was determined that the data generated by both the wind tunnel and the computer model were found to be similar to and representative of a true free-air airfoil. For further analysis, it is recommended to use the numerical results to model the linear region between minus twelve degrees and thirteen degrees, while the experimental results should be used for the end regions. These regions in the models accurately represent what one would expect from the airfoil used by the industry.2. IntroductionA recent development in airfoil design has seen a set of standardized airfoil designs that can be used in a wide range of applications...... middle of paper ...... revealed that lift maximum was 1.49. The positive and negative stall angles were also found to be similar in both tests, sixteen and fourteen from the numerical results and negative fourteen and negative twelve in the experimental test. From these two tests, it was found that the numerical results were a better representation of the linear region between negative twelve degrees and thirteen degrees, while the experimental results were a good fit for the end regions. These regions in the models accurately represent what one would expect from the airfoil used in the industry. The lab showed that while neither model perfectly represents how an airfoil will perform in a free air environment, the combination of a corrected wind tunnel test and the computer analysis program XFOIL can be used to get the most accurate representation of what will happen.