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Study of Aerodynamic Characteristics of a Spiroid Winglet


Affiliations
1 Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
     

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In this paper the effect of spiroid winglet on aerodynamic efficiency was investigated. A sweptback and tapered wing with NACA 0015 airfoil section was considered as base geometry. Above wing is modified by providing spiroid winglet at the tip of wing. Velocity of 35 m/s was taken to simulate this. CFD code was use to carry out the computation. The simulated results were compared with experimental result to validate the CFD code. In this process tangential velocity, lift coefficient and drag coefficient were computed initially. The simulations obtained from the CFD code show a very good agreement with the experimental results. The aerodynamics parameters were calculated at different geometric angle of attack (4°, 8°, 12° and 16°). The numerical results were compared with the result of base line model to find out the effect of spiroid winglet. It was observed the drag is reduced by using spiroid winglet.

Keywords

Tip-Vortex, Spiroid Winglet, Drag, Wingtip, Induced Drag.
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  • Study of Aerodynamic Characteristics of a Spiroid Winglet

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Authors

S. K. Singh
Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
S. K. Samal
Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India
S. Dash
Aeronautical Department, Bhubaneswar Engineering College, Bhubaneswar, Odisha, India

Abstract


In this paper the effect of spiroid winglet on aerodynamic efficiency was investigated. A sweptback and tapered wing with NACA 0015 airfoil section was considered as base geometry. Above wing is modified by providing spiroid winglet at the tip of wing. Velocity of 35 m/s was taken to simulate this. CFD code was use to carry out the computation. The simulated results were compared with experimental result to validate the CFD code. In this process tangential velocity, lift coefficient and drag coefficient were computed initially. The simulations obtained from the CFD code show a very good agreement with the experimental results. The aerodynamics parameters were calculated at different geometric angle of attack (4°, 8°, 12° and 16°). The numerical results were compared with the result of base line model to find out the effect of spiroid winglet. It was observed the drag is reduced by using spiroid winglet.

Keywords


Tip-Vortex, Spiroid Winglet, Drag, Wingtip, Induced Drag.

References