Stall Mitigation and Lift Enhancement of NACA 0012 with Triangle-Shaped Surface Protrusion at a Reynolds Number of 10<sup>5</sup>

Bodavula, Aslesha; Yadav, Rajesh; Güven, Uğur

doi:10.4271/01-12-02-0007

Cited by 4 publications

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“…Numerical investigation done on the triangular cavity type by Bodavula A, helped gain valuable insights on the effect of adding either cavity and protrusions on the cavity on the airfoil body also helped choose a pre-existing design for the test airfoil [17,18,19]. Provided the research on the solver model done by the former, which employs transition Shear Stress Transport equations to stabilize the solution with the transport equations, this is deemed as an efficient method for getting accurate results in a fluid simulation [20,21]. Studying airfoil with NACA 0012 profile to determine the drag characteristics also provided valuable insights helping ease the understanding on behavior of airfoil protrusions in different angles of attacks at different fluid flow properties [22].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Teja,

Bodavula,

Dussa

2023

ijmst

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Effects of a low Reynolds number flow on an airfoil with cavities of a specified shape are analyzed computationally to assess the aerodynamic performance by observing the coefficients of lift and drag with increasing angles of attacks. The Reynolds number considered for the simulation is 1×104 operating at atmospheric conditions at sea level. Indentations with a definite shape (right-angled triangle) are utilized to find the vortex effects of air in the cavity on the shear layer separation on airfoil surface to retain the flow even at higher angles of attack. The simulation is run in ANSYS Fluent to study the increase in the aerodynamic performance, research findings include an increase in coefficient of lift values by approximately, 111.86% of cavity with depth 0.05C indented at 70% of the chord length at 6° angle of attack, 68.13% of cavity with depth 0.05C indented at 50% of chord length at 6° angle of attack, 23.93% of cavity with depth 0.025C indented at 70% of chord length at 6° angle of attack, 3.96% of cavity of depth 0.025C at 6° angle of attack, 9.59% of cavity of depth 0.05C at 18° angle of attack.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Teja,

Bodavula,

Dussa

2023

ijmst

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“…The complex aerodynamic phenomena at lower Reynolds numbers have inspired many researchers to study and understand various flow control mechanisms. 19,20,21 Mainly, there are two types of flow control mechanisms, viz., passive flow control mechanism and active flow control mechanism. In the passive flow control mechanism, flow is controlled through non-energy consuming devices like vortex generators, flaps and slots.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the effect of triangular cavity on the unsteady aerodynamics of NACA 0012 at a low Reynolds number

Yadav

Bodavula

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Time accurate numerical simulations were conducted to investigate the effect of triangular cavities on the unsteady aerodynamic characteristics of NACA 0012 airfoil at a Reynolds number of 50,000. Right-angled triangular cavities are placed at 10%, 25% and 50% chord location on the suction and have depths of 0.025c and 0.05c, measured normal to the surface of the airfoil. The second-order accurate solution to the RANS equations is obtained using a pressure-based finite volume solver with a four-equation transition turbulence model, γ–Re θt, to model the effect of turbulence. The two-dimensional results suggest that the cavity of depth 0.025c at 10% chord improves the aerodynamic efficiency ( l/d ratio) by 52%, at an angle of attack of α = 8°, wherein the flow is steady. The shallower triangular cavity when placed at 25%c and 50%c enhances the l/d ratio by only 10% and 17%, respectively, in the steady-state regime of angles of attack between α = 6° and 10°. The deeper cavity also enhances the l/d ratio by up to 13%, 22% and 14% at angles of attack between α = 6° and 10°. Even in the unsteady vortex shedding regime, at α =12° and higher, significant improvements in the time-averaged l/d ratios are observed for both cavity depths. The improvements in l/d ratio in the steady-state, pre-stall regime are primarily because of drag reduction while in the post-stall, unsteady regime, the improvements are because of enhancements in time-averaged C l values. The current finding can thus be used to enhance the aerodynamic performance of MAVs and UAVs that fly at low Reynolds numbers.

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Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

Mohamed

Yadav

Güven

2021

AEAT

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Purpose This paper aims to achieve an optimum flow separation control over the airfoil using a passive flow control method by introducing a bio-inspired nose near the leading edge of the National Advisory Committee for Aeronautics (NACA) 4 and 6 series airfoil. In addition, to find the optimised leading edge nose design for NACA 4 and 6 series airfoils for flow separation control. Design/methodology/approach Different bio-inspired noses that are inspired by the cetacean species have been analysed for different NACA 4 and 6 series airfoils. Bio-inspired nose with different nose length, nose depth and nose circle diameter have been analysed on airfoils with different thicknesses, camber and camber locations to understand the aerodynamic flow properties such as vortex formation, flow separation, aerodynamic efficiency and moment. Findings The porpoise nose design that has a leading edge with depth = 2.25% of chord, length = 0.75% of chord and nose diameter = 2% of chord, delays the flow separation and improves the aerodynamic efficiency. Average increments of 5.5% to 6° in the lift values and decrements in parasitic drag (without affecting the pitching moment) for all the NACA 4 and 6 series airfoils were observed irrespective of airfoil geometry such as different thicknesses, camber and camber location. Research limitations/implications The two-dimensional computational analysis is done for different NACA 4 and 6 series airfoils at low subsonic speed. Practical implications This design improves aerodynamic performance and increases the structural strength of the aircraft wing compared to other conventional high lift devices and flow control devices. This universal leading edge flow control device can be adapted to aircraft wings incorporated with any NACA 4 and 6 series airfoil. Social implications The results would be of significant interest in the fields of aircraft design and wind turbine design, lowering the cost of energy and air travel for social benefits. Originality/value Different bio-inspired nose designs that are inspired by the cetacean species have been analysed for NACA 4 and 6 series airfoils and universal optimum nose design (porpoise airfoil) is found for NACA 4 and 6 series airfoils.

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Stall Mitigation and Lift Enhancement of NACA 0012 with Triangle-Shaped Surface Protrusion at a Reynolds Number of 10⁵

Cited by 4 publications

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Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Numerical investigation of the effect of triangular cavity on the unsteady aerodynamics of NACA 0012 at a low Reynolds number

Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

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Stall Mitigation and Lift Enhancement of NACA 0012 with Triangle-Shaped Surface Protrusion at a Reynolds Number of 105

Cited by 4 publications

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Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach

Numerical investigation of the effect of triangular cavity on the unsteady aerodynamics of NACA 0012 at a low Reynolds number

Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils

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Stall Mitigation and Lift Enhancement of NACA 0012 with Triangle-Shaped Surface Protrusion at a Reynolds Number of 10⁵