Reynolds Number Effect of Leading Edge Tubercles on Airfoil Aerodynamics

Peristy, Luke H.; Perez, Ruben E.; Asghar, Asad; Allan, W.

doi:10.2514/6.2016-3260

Cited by 22 publications

(2 citation statements)

References 22 publications

(31 reference statements)

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“…These sinusoidal protrusions at the leading edge are favorable only in the post stall regime, for conventional NACA 4-digit airfoils [18]. The improvements in post stall aerodynamic characteristics and stalling angle progress more with increasing Reynolds number in the range 75000-300000 [19]. In spite of that there is a necessity to explore about the pioneering passive flow control devices that can markedly enrich the performance of the Wind turbines and MAVs.…”

Section: Fig1: Flight Speed Versus Chord Reynolds Number [1]mentioning

confidence: 99%

Numerical Analysis of Protrusion Effect over an Airfoil at Reynolds Number -105

Bodavula¹,

GUVEN²,

Yadav³

2019

IJRTE

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Need of micro aerial vehicles and Unmanned AirVehicles is increasing due to military, defense and civilian requirements. These vehicles fly at very small Reynolds numbers and have to move in confined spaces with a bare minimum speed, to achieve high lift coefficient is the main concern. The main focus of this research paper is to carry out the computational analysis and study the unsteady flow over NACA0012 airfoil with right angle triangular protrusion at the Reynolds number 10 5 . The location of the protrusion is 0.05c, with three different heights of protrusion 0.005c, 0.01c, and 0.02c, normal to the surface of the airfoil. Geometric modeling and grid generation are created using the ICEM CFD software and numerical analysis carried out using CFD Software at various angle of attacks ranging from 0 0 to 16 0 with 2 0 intervals. Numerical validation has done and compared. The results obtained from the research work is recommend that for smaller protrusions the lift and drag coefficients are unaffected in the low angle of attacks while the lift characteristic is significantly improved at the higher angle of attacks.Numerical Analysis of Protrusion Effect over an Airfoil at Reynolds Number -10 5 2584 Fusion Technologies, advanced nuclear methods. He has written over 50 papers, 30 opinion articles and 4 books on future of space technology and nuclear technology. Dr. Guven has taught wide range of courses and he is coordinator in an Experimental Nanosatellite project.

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Section: Fig1: Flight Speed Versus Chord Reynolds Number [1]mentioning

confidence: 99%

Numerical Analysis of Protrusion Effect over an Airfoil at Reynolds Number -105

Bodavula¹,

GUVEN²,

Yadav³

2019

IJRTE

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“…Larger gap between the tubercles leads to a drop in aerodynamic efficiency of the airfoils (Serson and Meneghini, 2015). The enhancements in post-stall aerodynamic characteristics and increase in stalling angle strengthens further with increasing Reynolds number in the range 75,000-300,000 (Peristy et al, 2016). In addition, these protrusions perform better on thicker airfoils as compared to thinner ones (Paula et al, 2016).…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the unsteady aerodynamics of NACA 0012 with suction surface protrusion

Bodavula

Yadav

Güven

2019

AEAT

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Purpose The purpose of this paper is to investigate the effect of surface protrusions on the flow unsteadiness of NACA 0012 at a Reynolds number of 100,000. Design/methodology/approach Effect of protrusions is investigated through numerical simulation of two-dimensional Navier–Stokes equations using a finite volume solver. Turbulent stresses are resolved through the transition Shear stress transport (four-equation) turbulence model. Findings The small protrusion located at 0.05c and 0.1c significantly improve the lift coefficient by up to 36% in the post-stall regime. It also alleviates the leading edge stall. The larger protrusions increase the drag significantly along with significant degradation of lift characteristics in the pre-stall regime as well. The smaller protrusions also increase the frequency of the vortex shedding. Originality/value The effect of macroscopic protrusions or deposits in rarely investigated. The delay in stall shown by smaller protrusions can be beneficial to micro aerial vehicles. The smaller protrusions increase the frequency of the vortex shedding, and hence, can be used as a tool to enhance energy production for energy harvesters based on vortex-induced vibrations and oscillating wing philosophy.

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