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- W3048385835 abstract "A naval fighter aircraft has conflicting demands for achieving low speed for landing on an aircraft carrier with minimum compromise on high-speed and supersonic capabilities. A sharp leading edge surface called LEVCON that can be deflected upwards for reducing approach speed has been implemented on an indigenous naval aircraft. Another solution explored in this paper is to vertically extend a panel near the wing apex called vortex flap to achieve increase in trim lift coefficient. It shows enhanced performance and improved aerodynamic characteristics for better handling qualities, without impacting high-speed flight. CFD simulations are run for a number of flap profiles, and the preferred family of shapes is identified for optimization by parameterizing six design variables. Some selected vortex flap geometries were then tested in a wind tunnel, and the results indicate that the approach speed target is met within all identified constraints. It is now planned to flight test the preferred shape for confirming the practical application of this concept on future naval aircraft designs." @default.
- W3048385835 created "2020-08-18" @default.
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- W3048385835 date "2020-01-01" @default.
- W3048385835 modified "2023-09-27" @default.
- W3048385835 title "Design of Vortex Flaps for Reducing Approach Speed of a Supersonic Naval Fighter Aircraft" @default.
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- W3048385835 doi "https://doi.org/10.1007/978-981-15-5432-2_9" @default.
- W3048385835 hasPublicationYear "2020" @default.
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