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

Bodavula, Aslesha; Yadav, Rajesh; Güven, Uğur

doi:10.1108/aeat-01-2019-0022

Cited by 5 publications

(5 citation statements)

References 51 publications

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“…Meanwhile, for airfoil empennage, NACA 0009 was used as airfoil data obtained from the UIUU Catalog [8], [14]. This data is then revalidated with the help of XFRL5 software and comparison with relevant research [3], [16].…”

Section: Methodsmentioning

confidence: 99%

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Rapid Preliminary Sailplane Design using Regression Method

Yamin

Giyats

2022

JNEST

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The article describes a new method for the preliminary design of a Sailplane based on technical data from similar Sailplanes, enabling quick design using regression methods. The authors chose FX 66-168 as the main wing airfoil for a new sailplane with a gross weight of 602 kg with a flight parameter Angle-of-Attack (AoA) 00 in minimum velocity of 49.5 m/s to cruise. As an example, we illustrate the proposed regression method. Our method allows for improving the effective preliminary design of the sailplane. The effectiveness evaluation validation of the new model is conducted with the numerical calculation using XFLR Opensource software. The research results improve design techniques and could be used as a manual for an aircraft designer.

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Section: Methodsmentioning

confidence: 99%

“…The cirrus sailplane is designed with two different airfoils. One of the examples of a cirrus sailplane is FX 66-27 ALL-182, designed by Dr. FX Wortmann at the University of Stuttgart [3]. Later, computer-aided software is employed to assist glider designs in improving performance [4].…”

Section: Introductionmentioning

confidence: 99%

Rapid Preliminary Sailplane Design using Regression Method

Yamin

Giyats

2022

JNEST

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“…It was observed that airfoil with a nose having a shorter length and medium depth shows a noticeable increase in aerodynamic efficiency almost at all angles of attack (Arif et al , 2019). It has also been reported that triangular protrusion at the leading edge can significantly enhance the lift produced by an airfoil (Bodavula et al , 2019). They also showed that at low Reynolds number the pre-stall aerodynamic characteristics of National Advisory Committee for Aeronautics (NACA) 0012 is greatly improved and the stall is mitigated with smaller protrusion near the leading edge (Bodavula et al , 2019).…”

Section: Introductionmentioning

confidence: 93%

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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“…Although many researchers have attempted to use different types of indentations of different sizes, depths, and placement types, both above and below a surface, to summarize this, the depths of a single type of cavity can be tested on different regions of an airfoil surface. 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].…”

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

Cited by 5 publications

References 51 publications

Rapid Preliminary Sailplane Design using Regression Method

Rapid Preliminary Sailplane Design using Regression Method

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

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

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