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Abstract— The aerodynamic performance of a wing is
strongly influenced by boundary layer separation,
especially at higher angles of attack. In the present study, a
numerical investigation is carried out to analyze the effect
of surface dimples on the flow separation characteristics of
a NACA 4412 wing. Two configurations, namely a smooth
wing and a dimpled wing, are modeled and analyzed using
ANSYS Fluent. The simulations are performed at a free
stream velocity of 20 m/s for angles of attack of 0°, 4°, 8°,
12°, and 16°. The aerodynamic performance is evaluated in
terms of lift coefficient, drag coefficient, lift force, and drag
force. The results indicate that the dimpled wing exhibits
slightly improved lift characteristics and delayed flow
separation compared to the smooth wing at higher angles of
attack. The study shows that surface dimples can act as a
passive flow control technique for enhancing aerodynamic
performance at low Reynolds number conditions.
"Numerical Investigation of Flow Separation Control on a NACA 4412 Wing Using Surface Dimples ", International Journal for Research Trends and Innovation (www.ijrti.org), ISSN:2456-3315, Vol.11, Issue 3, page no.a576-a583, March-2026, Available :http://www.ijrti.org/papers/IJRTI2603074.pdf
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2456-3315 | IMPACT FACTOR: 8.14 Calculated By Google Scholar| ESTD YEAR: 2016
An International Scholarly Open Access Journal, Peer-Reviewed, Refereed Journal Impact Factor 8.14 Calculate by Google Scholar and Semantic Scholar | AI-Powered Research Tool, Multidisciplinary, Monthly, Multilanguage Journal Indexing in All Major Database & Metadata, Citation Generator