A study on performance of surface modified NACA 2412 airfoil at various Reynolds number and angle of attacks
Authors
-
,IN
Rakesh C M -
,INYogesh Shankar R P
-
,INNiranjan Hiremath
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,INHarshith J N
-
,INTejas Thalekar
-
,INDhanush D R
DOI:
https://doi.org/10.18311/jmmf/2021/30115Keywords:
NACA, airfoil, angle of attack, Reynolds number.Abstract
In the present investigation, aerodynamic performance study of NACA 2412 airfoil with surface modifications for the enhanced optimized aerodynamic characteristics is carried out. Three airfoils were built by introducing the cut at different locations. The present work is a computational analysis of the effect of inward cut on the lower surface of airfoil at 25%, 50%, and 75% chord length. The study parameters include flow separation (or stall), lift, drag, and angle of attack. The model is developed in Ansys design modeler and meshed in ICEMCFD. All three meshed models are simulated at 0o, 40o, 80o, 120o and 16o angle of attacks (AoA) at 60000 and 100000 (1 lakh) Reynolds number. The post processing revealed that, the increase in AoA resulted in increase in lift co-efficient (CL) for all three airfoils at both Reynolds number. The lift coefficient started increasing as the position of cut moved towards the trailing edge. The flow started separating after 12o AoA. It was found that, the airfoil with inward cut at 75% of chord length resulted in attaining highest lift co-efficient when compared to other two airfoils.
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Accepted 2022-04-28
Published 2022-04-28
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