High lift airfoil database4/24/2024 ![]() Two distinct types of hysteresis in reattachment were observed. Once the flow was separated, the separation point moved upstream and the suction peak decreased in magnitude with increasing Reynolds number. The stall angle and the maximum lift coefficient increased with Reynolds number. ![]() As the Reynolds number was increased beyond this value, the stall type gradually shifted from trailing-edge stall to leading-edge stall. A fundamental change in the flow behaviour was observed around Re_c= 2.0 × 10^6. As such, attached and separated conditions, as well as the static stall and reattachment processes were studied. The angle of attack was incrementally increased and decreased over a range of 0° ≤ alpha ≤ 40°, spanning both the attached and stalled regime at all Reynolds numbers. The use of a high-pressure wind tunnel allowed for variation of the chord Reynolds number over a range of 5.0 × 10^5 ≤ Re_c ≤ 7.9 × 10^6. It was proven that SimFlow is capable of predicting with high accuracy lift and drag. Reynolds number effects on the aerodynamics of the moderately thick NACA 0021 airfoil were experimentally studied by means of surface-pressure measurements. data and simulation results from other CFD codes, provided by NASA. National Defense Science and Engineering Graduate Fellowship National Science Foundation grant CBET 1652583 Static measurements of a NACA 0021 airfoil at high Reynolds numbers Please use this identifier to cite or link to this item: Princeton University Undergraduate Senior Theses, 1924-2023 Princeton University Masters Theses, 2022-2024 Princeton University Doctoral Dissertations, 2011-2024 Princeton School of Public and International Affairs ![]() Liechtenstein Institute on Self-Determination Lewis-Sigler Institute for Integrative Genomics Department of Slavic Languages and Literatures
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