Self-noise effects on aerodynamics of cambered airfoils at low reynolds number

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[1] Ikeda, Tomoaki

[2] Atobe, Takashi

[3] Fujimoto, Daisuke

[4] Inasawa, Ayumu

[5] Asai, Masahito

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| 1600年 / AIAA International, 12700 Sunrise Valley Drive, Suite 200Reston, VA, Virginia, Virginia 20191-5807, United States卷 / 53期

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Aerodynamics of cambered airfoils are investigated numerically; using aNACAfour-digit series of6%thickness at low Reynolds number Re = 10; 000 and moderate Mach numberM = 0.2; by focusing on the relation of aeroacoustic effects and hydrodynamic flow unsteadiness. Two-dimensional numerical simulations show that the onset of an acoustic feedback loop leads to an abrupt increase in lift force. Associated with the feedback process; the evolution of two-dimensional vortices in the suction-side boundary layer shifts a separation bubble toward the leading edge; which causes a relatively steep pressure recovery near the trailing edge. Through a parametric study on airfoil shape; the aerodynamically favorable feature of aft camber is further enhanced with the presence of an acoustic feedback loop. In addition; the aft camber airfoil successfully forms a laminar separation bubble in three-dimensional calculations at the present Reynolds number; developing transitional behavior on the suction side; supposedly prompted by the airfoil tones. Although the boundary layer shows three-dimensional complexity; still the formation of an acoustic feedback loop is strongly suggested; via the comparison of spanwise correlations. © 2014 by the American Institute of Aeronautics and Astronautics; Inc. All rights reserved;

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