Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps

Nilavarasan, T.; Joshi, Ganapati; Chandel, Sunil

doi:10.1515/tjj-2018-0012

Cited by 7 publications

(3 citation statements)

References 13 publications

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“…Each source or sink has specific strength, K and vortex strength denoted by circulation, Г . Simple 2 D uniform lifting flows (Haughton and Carpenter, 2011; Jain et al , 2020; Nilavarasan et al , 2018) can be described using the streamline and velocity potential functions as equation (1) and equation (2): …”

Section: Methodsmentioning

confidence: 99%

Aerodynamic flow modelling of NACA 0010 using 2D panel and Jukouwski methods

Bhargava¹,

Maddula²,

Neigapula

et al. 2022

AEAT

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Purpose This paper aims to model the aerodynamic flow characteristics of NACA0010 for various angle of attacks including stall for incompressible flows using panel methods. This paper also aims to quantify the surface pressure distribution on streamlined bodies and validate the results with analytical Jukouwski method and inverse panel methods that can predict the aerodynamic flow behaviour using the geometric iteration approach. Design/methodology/approach The 2 D panel method was implemented in Qblade software v.06 which uses the fundamental panel method which rely on source strengths and influence coefficients to determine the velocity and pressure fields on the surface. The software implements the boundary layer or viscous effects to determine the influence on aerodynamic performance at various angles of attack. Jukouwski method is also evaluated for predicting aerodynamic characteristics and is based on the geometric iteration approach. Then complex aerodynamic flow potentials are determined based on the source strengths which are used to predict the pressure and velocity fields. Findings At low to moderate angles of attack, panel and Jukouwski methods predict similar results for surface pressure coefficients comparable to Hess and Smith inverse method. In comparison to panel method, results from the Jukouwski mapping method predicted the pressure coefficient conservatively for the same free stream conditions. With increase in Reynolds number, lift coefficient and aerodynamic performance improved significantly for un-tripped aerofoil when stall angle is approached when compared to tripped aerofoil. Practical implications This study demonstrated that panel methods have higher efficacy in terms of computational time or resources and thus can provide benefits to many real-world aircraft or aerospace design applications. Originality/value Even though panel and Jukouwski methods have been studied extensively in the past, this paper demonstrates the efficacy of both methods for modelling aerodynamic flows that range between moderate to high Reynolds number which are critical for many aircraft applications. Both methods have been validated with analytical and inverse design methods which are able to predict aerodynamic flow characteristics for simple bluff bodies, streamlined aerofoils as well as bio-inspired corrugated aerofoils.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic flow modelling of NACA 0010 using 2D panel and Jukouwski methods

Bhargava¹,

Maddula²,

Neigapula

et al. 2022

AEAT

View full text Add to dashboard Cite

show abstract

“…Each source or sink has specific strength, K, and vortex strength denoted by circulation, Г. Simple 2D uniform lifting flows 14,17,18 can be described using the stream line and velocity potential functions as Eq. ( 7) and Eq.…”

Section: Panel Methodsmentioning

confidence: 99%

Computational analysis of NACA 0010 at moderate to high Reynolds number using 2D panel method

Maddula¹,

Bhargava²,

Padhy³

et al. 2020

MOJABB

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Wing structures as found in aircrafts and wind turbine blades are developed using airfoils. Computational methods are often used to predict the aerodynamic characteristics of such airfoils, typically the pressure, lift and drag force coefficients. In the present work, surface pressure coefficient distribution of NACA 0010 is evaluated using the 2D panel and Jukouwski methods for incompressible lifting flows for three Reynolds numbers, Re–3 x105, 5 x105, 1 x 106. The analysis was conducted for various AOA (angle of attack), between –20 to 100 for the airfoil with tripped and untripped conditions. The non–dimensional pressure coefficient along chord direction of airfoil is illustrated for upper and lower surfaces between –20 to 100 angle of attack. The coefficient of lift and drag as well as glide ratio are evaluated for all three Reynolds numbers. The present results from the 2D panel method are validated using the results from Hess and Smith, inverse design methods implemented on conformal mapped symmetric Jukouwski airfoil of 10% thickness to chord at 40 angle of attack.

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“…The GF has proven to have interesting implications in a wide range of fields. The work by Wang et al [27], as well as that of Troolin [23], indeed provides an extensive overview of the GF applications, which include both low and high-speed airfoils [28], aircrafts, wings, helicopter rotors [29] and, recently, wind turbines. Focusing on this latter application, many literature instances suggest the GF as a promising device not only for active flow control [30][31][32][33][34][35], but also for turbine performance increase [36][37][38].…”

Section: Aim and Methodsmentioning

confidence: 99%