Please use this identifier to cite or link to this item: http://hdl.handle.net/10603/232725
Title: Aerodynamic Performance And Stability Analysis Of Bio_Inspired Corrugated Wings For Micro Air Vehicles
Researcher: Yagya Dutta Dwivedi
Guide(s): P.M.V Rao, Donepudi Jagadish
Keywords: Engineering and Technology,Engineering,Engineering Mechanical
University: Vignans Foundation for Science Technology and Research
Completed Date: 2018
Abstract: Micro air vehicles (MAVs) are becoming fascinating day by day which can be used for military and civil purposes. These vehicles are mostly used for reconnaissance, surveillance, search and rescue, disaster management and recreational purposes. The most common MAVs are of the flapping and rotary wing configuration. The aerodynamics of flapping wing MAVs are like wings of insects, which generate lift and thrust being small size less than 10 cm and low speed less than 20 m/s (low Reynolds numbers). Insects fly in all types of environmental conditions with its high agility and maneuverability. To build efficient and small MAVs the insect flight need to be further investigated. It is observed that the insect s wings are not smooth as conventional one but has some form of well tuned corrugations. newline newlineThis study is intended to understand the effect of low Reynolds number (Re) flows related to bio-inspired wing corrugation for possible application in MAVs. Three wings profiles i.e. Corrugated A, Corrugated B and Flat Plate were fabricated to undertake the experimental work in a subsonic wind tunnel. Aerodynamic forces like lift, drag and moments were measured by using strain gauge balance. The measurements of moments were done in all the three axes (longitudinal, lateral and vertical axes) to find static stability of all three tested wings. The tuft and smoke flow visualization were employed on all the three types of wings to understand the flow behaviour like wing stall, flow reversal and spanwise flow. Twenty Probe Rake measured boundary layer velocities at three different semispan locations (30%, 60% and 90% of the semispan) at a fixed chord length of 70% from leading edge (0.7 c) with range of angles of attack (AOA) and Re. The static longitudinal, lateral and directional stability of a Flat Plate, Corrugated A and Corrugated B wings were assessed experimentally and result showed that Flat Plate wing possess better static stability than Corrugated A and Corrugated B wings.
Pagination: 200
URI: http://hdl.handle.net/10603/232725
Appears in Departments:Department of Mechanical Engineering

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