Wind and Structures

  • 제29권4호
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  • Pages.271-277
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  • 2019
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  • 1226-6116(pISSN)
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  • 1598-6225(eISSN)
테크노프레스 (Techno-Press)
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DOI QR코드

DOI QR Code

Enhancing aerodynamic performance of NACA 4412 aircraft wing using leading edge modification

  • Kumar, B. Ravi (School of Mechanical Engineering, SASTRA Deemed University)
  • 투고 : 2018.11.11
  • 심사 : 2019.09.02
  • 발행 : 2019.10.25
⟨ 이전 논문 다음 논문 ⟩

초록

This work deals with designing the aircraft wing and simulating the flow behavior on it to determine the aerodynamically efficient wing design. A NACA 4412 airfoil is used to design the base wing model. A wing with a rectangular planform and the one with curved leading edge planform was designed such that their surface areas are the same. Then, a comprehensive flow analysis is carried out at various velocities and angle of attacks using computational fluid dynamics (CFD) and the results were interpreted and compared with the experimental values. This study shows that there is a significant improvement in the aerodynamic performance of the curved leading edge wing over the wing with rectangular planform.

키워드

참고문헌

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