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- W2557236721 abstract "This paper attempts to bring out the challenges associated with the design of a high altitude mini UAV especially from the aerodynamics perspective. The mini UAV under consideration is a 2 kg class conventional, high wing and T-Tail configuration. A comparative study of various high lift airfoils has been done to illustrate that the selection of a suitable airfoil for high altitude applications is indeed an important part of the design activity and it shows that the wing loading of a UAV designed for high altitudes does not depend on the changes in air density alone. The chosen high lift low Reynolds number airfoil is found to have a minor effect on the aerodynamic parameters (Cl and Cd) with changes in Reynolds number. This paper also addresses the performance variation due to operation at off design condition such as at sea level." @default.
- W2557236721 created "2016-12-08" @default.
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- W2557236721 date "2013-01-01" @default.
- W2557236721 modified "2023-09-22" @default.
- W2557236721 title "Design of a High Altitude Fixed Wing Mini UAV - Aerodynamic Challenges" @default.
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