Modelling the time dependent flow over riblets in the viscous wall region

Tullis, S.; Pollard, A.

doi:10.1007/bf00850563

Cited by 10 publications

(1 citation statement)

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“…Another study noted that the riblets lessen momentum transfer by reducing the vortices and cross flow velocity in the turbulent region. This influenced the turbulence to become less intense and postponed the transition to turbulence [22,23]. Hence, in this research, an attempt was made to reduce the drag on a subsonic NACA 2412 wing using riblets.…”

Section: Introductionmentioning

confidence: 99%

NACA 2412 Drag Reduction Using V-Shaped Riblets

Selvanose,

Marimuthu,

Awan

et al. 2024

Eng

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This research focuses on addressing a significant concern in the aviation industry, which is drag. The primary objective of this project is to achieve drag reduction through the implementation of riblets on a wing featuring the NACA 2412 aerofoil, operating at subsonic speeds. Riblets, with the flow direction on wing surfaces, have demonstrated the potential to effectively decrease drag in diverse applications. This investigation includes computational analysis within the ANSYS Workbench framework, employing a polyhedral mesh model. The scope of this research encompasses the analysis of both a conventional wing and a modified wing with riblets. A comparative analysis is conducted to assess variations in drag values between the two configurations. Parameters, including geometry, dimensions, and riblet placement at varying angles of attack, are explored to comprehend their impact on drag reduction. Notably, 15.6% and 23% reductions in drag were identified at a 16-degree angle of attack with midspan and three-riblet models, separately. The computational mesh and method were validated using appropriate techniques.

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Section: Introductionmentioning

confidence: 99%