Experimental Study of the Wake behind an MAV using Hot-Wire Anemometer

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بررسی تجربی یک مدل ریزپرنده با استفاده از جریان سنج سیم داغ

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 42377 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza; Khoshnevis, Amir
Abstract:
In present thesis, experimental study of flow around a two-wing MAV using hot-wire anemometer will be performed which is divided to wake and boundary layer study. This leads to suitable understanding of various parameters affecting its wake and boundary layer. First, effects of upper wing, which has horizontal stabilizer's role, on the main wing's wake will be studied in which effects of angle of attack and distance between the two wings at its cruise velocity will be investigated. Then, effects of angle of attack, velocity and distance between wings on boundary layer of the MAV will be analyzed. Also, experiments are performed at three velocities as 10, 15 and 20 m/s, and three angles of attack as zero, 2 and 4 degree. Results show that existence of upper wing will affects the main wing's wake and as distance between two wings decreases, their wake interaction will increases, it means that the two wake will merge in together. Also, the horizontal stabilizer decreases the main wing's boundary layer thickness
Keywords:
Wakes ; Boundary Layer ; Hot-Wire Anemometry ; Micro Air Vehicle (MAV)

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