The model is more accurate and the computation time required is less.
Transition SST uses four transport equations to model the transition behavior which has been clearly explained in previous work of Aftab et al. It has been well proven and designed for low Reynolds number aerodynamic applications.
Velocity over an airfoil generator software#
Experimental testing in wind tunnel is also carried out, based on the best tubercle design.Ĭommercial simulation software ANSYS was used to carry out Steady state analysis considering, transition SST turbulence model. This study is unique as an in-depth study comparing, tubercle design has not been reported in literature. A parametric study is carried out between the two designs by varying the tubercle amplitude, inorder to determine which design is more suitable for NACA 4415 airfoil. The current study is on NACA 4415 airfoil profile with sinusoidal and spherical TLE. The work on transition SST turbulence model reported by Langtry and Menter and Menter et al., is quite accurate to capture the separation bubble and other related phenomenon for low Reynolds number flows. Five turbulence models were tested in the study, out of all RANS turbulence models tested, only transition SST turbulence model is suitable to capture the transition effects.
Gawad conducted CFD study on NACA 0012 implementing spherical TLE and reported that, it performed better compared to the sinusoidal TLE.Īftab et al., also carried out a numerical study for low Reynolds number flow. Only one author Gawad has proposed spherical TLE design. The above mentioned researchers as well as few others, such as Custodio et al.,, Rostamzadeh et al.,, Miklosovic et al.,, Borg, Corsini et al,, Zhang et al., and Skillen et al.,, have worked considering only the sinusoidal tubercles designs. Chen et al., further investigated the effect of tubercles on a highly swept delta wing. Chen et al., investigated the effect of the tubercles on the performance of a moderately swept delta wing. Goruney and Rockwell, studied the effect of TLE on a swept delta wing.Kim et al., extended the previous study of Yoon et al.,, studying the effect of 5 wavelengths (, ,, and, S is span 1.5c) for fixed amplitude (0.5c). Yoon et al., studied the effect of waviness along the span, for 5 different waviness ratios (0.2, 0.4, 0.6, 0.8 and 1.0), in comparison with base line airfoil.Custodio et al., studied four planform geometries: rectangular finite span, infinite span, swept and idealized flipper model.
A detailed review on application of Humpback whale flipper design on various airfoils has been conducted by Aftab et al. Implementing tubercle design has shown to improve airfoil performance, dratstically reduce aeroacoustic noise and seperation bubble. Research utilizing Humpback whale tubercles has gained popularity over the past decade. This is an open access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.ĭata Availability: All relevant data are within the paper and its Supporting Information files.įunding: The authors would like to acknowledge the support provided by the Ministry of Science, Technology and Innovation (MOSTI), Malaysia, for providing funds through the e-science fund, grant no 04-01-04-SF2206, for the current research.Ĭompeting interests: The authors have declared that no competing interests exist.īiomimetics is the art of studying and applying nature inspired designs in the field of engineering. Received: NovemAccepted: AugPublished: August 29, 2017Ĭopyright: © 2017 Aftab, Ahmad. PLoS ONE 12(8):Ĭoastal Carolina University, UNITED STATES Citation: Aftab SMA, Ahmad KA (2017) CFD study on NACA 4415 airfoil implementing spherical and sinusoidal Tubercle Leading Edge.
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