The Low Speed Aerodynamic Analysis of Segmental Wing Profile
Journal Title: International Journal of Mechanical and Production Engineering Research and Development (IJMPERD ) - Year 2019, Vol 9, Issue 4
Abstract
Generally, maximum angle of attack of a symmetric airfoil with downwash and up wash beyond which flow separation state is 16 degree. Un-symmetrical airfoil generates considerable amount of lift even at zero degree. Studies for improving efficiency of airfoil by delaying flow separation and increasing lift have been done in the past decades. Employing trailing edge flap, leading edge slot and slat are the result of those studies. Current studies dealing with lift optimization in airfoil is carried out by incorporating various proven and unproven methods. This study is focused on the bio-mimicking of eagle feather using overlap technique for low speed flows. Eagle is capable to alter its strategic arrangement for optimizing aerodynamics of the flow during any flight stage and irrespective of endurance, range and flow condition it varies flight level. Airfoil NACA series - S122, a subsonic sample has been selected for this proposed research. On the upper side of the wing surface a flexible aerodynamic feather has been attached for the experiments. Turbulence robust behavior is obtained by an airfoil which is flexible whereas uncontrollable behavior in turbulent stream is shown by conventional wing. Results showed that there is a significant affirmative variation in lift and followed by a full-fledged delay in the flow separation. Rectangular wings are generally characterized by gentle stall and a warning buffet prior to stall. Thus, a flexible feature wing can be employed to reduce the stall. This article will provide a different solution and thinking for young researchers working on low speed aerodynamics.
Authors and Affiliations
J. V. Muruga Lal Jeyan, Krishna S. Nair, Kavya S. Nair
Keywords
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- EP ID EP657029
- DOI 10.24247/ijmperdaug2019135
- Views 123
- Downloads 0
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