Prediction of Atmospheric Turbulence Characteristics for Surface Boundary Layer using Empirical Spectral Methods

Dwivedi, Yagya Dutta; Nukala, Vasishta Bhargava; Maddula, Satya Prasad; Nair, K. U.

doi:10.1590/0102-77863540083

Cited by 2 publications

(4 citation statements)

References 23 publications

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“…Such a flow condition increases the span wise aerodynamic loads significantly. Analysing turbulent boundary layer characteristics are thus useful for predicting the pressure and velocity field over aerofoil surfaces (Bhargava et al , 2018; Dwivedi et al , 2020; Naveen et al , 2020). In the present work, we analyse the surface pressure coefficient of NACA 0010 aerofoil using 2 D panel method and Jukouwski method for different flow conditions.…”

Section: Introductionmentioning

confidence: 99%

“…Several experiment studies were conducted on NACA aerofoil series by Abbott and Von Doenhoff to compare the aerodynamic characteristics for varying Mach and Reynolds number with free and forced boundary layer transitions (http://web.mit.edu/drela/Public/web/xfoil/ , Vargas et al , 2008). Both symmetric and cambered NACA aerofoil types were used by designers to improve maximum possible lift coefficient on wind turbine rotor blades as well as in marine propellers in ship industry (Craig and Huisjen, 2006; Dwivedi et al , 2020). Commercially available open source software like XFOIL utilize the 2 D source and vortex panel approximation methods coupled to boundary layer equations.…”

Section: Introductionmentioning

confidence: 99%

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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: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Bhargava¹,

Maddula²,

Neigapula

et al. 2022

AEAT

Self Cite

View full text Add to dashboard Cite

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“…4,5 Both symmetric and cambered NACA airfoil types are used by designers to improve maximum possible lift coefficient on wind turbine rotor blades as well as in marine propellers in ship industry. 6,7 Mark Drela at Massachussets Institute of Technology developed software known as XFOIL which is essentially an implementation of 2D panel method through an interactive program that can be readily used for aerodynamic design and analysis of subsonic airfoils. Commercially available online programs tools viz.…”

Section: Introductionmentioning

confidence: 99%

“…Analyzing turbulent boundary layer characteristics is useful for predicting the pressure and velocity field over airfoil surfaces as well as to quantify noise radiation from streamlined and bluff bodies. [7][8][9] In the present work, we analyze the surface pressure coefficient of NACA 0010 airfoil using 2D panel method and Jukouwski method for different flow conditions. An iterative numerical algorithm for 2D panel method is presented to evaluate the aerodynamic performance characteristics.…”

Section: Introductionmentioning

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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Prediction of Atmospheric Turbulence Characteristics for Surface Boundary Layer using Empirical Spectral Methods

Cited by 2 publications

References 23 publications

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

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

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

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