Effects of Reduced Frequency and Mean Angle of Attack on Pressure Distribution of a Supercritical Airfoil under Plunging Motion in Low-Subsonic Flow

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Zaynalzadeh, Aghil | 2013

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 48049 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza
Abstract:
A ten percent thick supercritical airfoil, having special previllage rather than conventional airfoils tested in a low speed wind tunnel to measure pressure distribution over the airfoil in steady and unsteady flow. Present thesis is set out to discuss effects of reduced frequency and mean angle of attack on pressure distribution during plunging motion in low-subsonic flow. Investigation of experimental data from frequency domain aspect is very challenging area in experimental aerodynamics. Therefore, the concepts of frequency domain analysis is pointed out. The analysis of experiment data is devidind in two different part, that is, steady and unsteady flow. Flow separation over the airfoil using pressure distribution is discussed first. Since all experimental data are deduced from pitching airfoil, a comparison between pitching and plunging pressure distribution is presented. Pressure transducer signals at sensitive regions on the airfoil are selecterd for frequency domain analysis. Finally, the results are compared and future studies are given
Keywords:
Unsteady Aerodynamic ; Pressure Distribution ; Frequency Analysis ; Hysteresis Ring ; Plunging ; Supercritical Airfoil

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