Airfoil database reynolds3/9/2024 ![]() Recently, and the subject of this paper, this model was retested in the same facility at Reynolds numbers down to 1.0 × 105. In addition to free-transition measurements, potential drag reductions using artificial turbulators were explored, although the benefits were found to be limited for this application. At that time, over two decades ago, to validate the design tools as well as the design itself, high-quality measurements of section characteristics and pressure distributions were made in the Penn State Low-Speed, Low-Turbulence Wind Tunnel from Reynolds numbers of 2.4 × 105 to 1.0 × 106. This design problem is difficult because this application requires the airfoil to operate over a wide range of Reynolds numbers, from roughly 0.7 × 105 to 1.0 × 106. ![]() N2 - The PSU 94-097 airfoil was originally designed in the early 1990’s for use on winglets of high-performance sailplanes. © 2021, American Institute of Aeronautics and Astronautics Inc. T1 - Experimental Results for a Low-Reynolds Number Airfoil in a Low-Turbulence Environment Finally, as was the case with the results obtained from the original tests, with the exception of the maximum lift coefficient, theoretical predictions using well-known codes are found to be in good agreement with the wind-tunnel measurements.", In addition, as this airfoil has also been successfully employed on model aircraft and UAVs, its performance using a simulated simple flap/aileron was also measured and found to be as expected and desired, that is, comparable with similar flapped-equipped airfoils. ![]() Finally, as was the case with the results obtained from the original tests, with the exception of the maximum lift coefficient, theoretical predictions using well-known codes are found to be in good agreement with the wind-tunnel measurements.Ībstract = "The PSU 94-097 airfoil was originally designed in the early 1990s for use on winglets of high-performance sailplanes. Recently, and the subject of this paper, this model was retested in the same facility at Reynolds numbers down to 1.0 × 10 5. At that time, over two decades ago, to validate the design tools as well as the design itself, high-quality measurements of section characteristics and pressure distributions were made in the Penn State Low-Speed, Low-Turbulence Wind Tunnel from Reynolds numbers of 2.4 × 10 5 to 1.0 × 10 6. This design problem is difficult because this application requires the airfoil to operate over a wide range of Reynolds numbers, from roughly 0.7 × 10 5 to 1.0 × 10 6. The PSU 94-097 airfoil was originally designed in the early 1990’s for use on winglets of high-performance sailplanes.
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