Study on Effect of Dimple on Aerodynamic Characteristics of NACA 0012 Airfoil

B M Saif; Sudipto Tushar Das; Gazi Faisal

doi:10.38032/scse.2026.4.174

Authors

B M Saif Military Institute of Science and Technology, Dhaka, Bangladesh
Sudipto Tushar Das Military Institute of Science and Technology, Dhaka, Bangladesh
Gazi Faisal Military Institute of Science and Technology, Dhaka, Bangladesh

DOI:

https://doi.org/10.38032/scse.2026.4.174

Keywords:

NACA 0012 Airfoil, Dimple Effect, FVM Method, k- ε Model

Abstract

This research uses FVM (Finite Volume Method) to examine the impact of profile modifications on a NACA-0012 airfoil. The profile adjustments being investigated consist of a circular dimple at the upper surface of the NACA-0012 airfoil at 50% of the chord length. This paper examines the values of coefficient of lift and drag, contours of pressure and velocity as these are the vital parameters, which are used as the parameters to do further calculations of airfoil performance, lift, drag etc. by using the k-ε model to observe the aerodynamic behaviour of the modified airfoil. Even though the airfoil's efficiency declines, the stall angle increases, causing flow separation to take longer. Validating the model is a challenge for this project. As a result, some ways to validation are used, while some other approaches are recommended for investigations in the future.

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References

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