Fourier series solution for inverse design of aerodynamic shapes

Dulikravich, George S.; Baker, Daniel P.

doi:10.1016/b978-008043319-6/50049-2

Cited by 7 publications

(5 citation statements)

References 3 publications

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“…The MGM procedure was incorporated into a multigrid Navier-Stokes airfoil analysis method in [15]. Dulikravich & Baker [16] formulated a Fourier series solution of the MGM equation. The MGM technique was applied in [17] for the inverse design of vertical axis wind turbine blades with constant thickness, which represents a geometry substantially different from those described by airfoils.…”

Section: Introductionmentioning

confidence: 99%

Inverse design of wind turbine blade sections for operation under icing conditions

Kollár

Mishra

2019

Energy Conversion and Management

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A methodology is developed to determine the shape of the two dimensional section of wind turbine blades considering the operation of wind turbine under icing conditions. An inverse design process provides the blade shape from a prescribed pressure or velocity distribution, and then the icing of the blade section obtained is simulated under different ambient conditions. The aerodynamic performances of the bare blade and the iced blade are evaluated and compared, which serves as the basis for involving a correction factor in the inverse design process. This correction factor modifies the prescribed velocity distribution so that the blade shape provided by the inverse design process will be applicable under some icing conditions that are chosen according to the prevailing meteorological conditions of the location where the wind turbine is installed. The procedure presented will contribute towards the design of blade shapes that can enable wind turbines to operate under a wide range of ambient conditions satisfactorily.

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Section: Introductionmentioning

confidence: 99%

Inverse design of wind turbine blade sections for operation under icing conditions

Kollár

Mishra

2019

Energy Conversion and Management

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“…This is the major disadvantage of the method as the success of inverse design depends on the specification of these arbitrary constants. For airfoil design the amount of β 1 =1.2, β 2 =0, β 3 =0.4 was considered which are the same values which was proposed by Dulikravich and Baker [11].…”

Section: Target Calculatedmentioning

confidence: 99%

“…The airfoil surface is treated as elastic membrane, which is modified based on the differences between target and calculated pressure coefficient. The airfoil modifying algorithm is based on the method of Dulikravich and Baker [11] who suggested the following linear partial differential equations can be used as a residual corrector to modify the top and bottom contour of the blade respectively: (7) and equation (8), s is the airfoil contour following coordinate, L E is the lower airfoil contour length, L is the total airfoil counter length and ∆y top and ∆y bottom are the blade normal displacement at the top and bottom counter of the airfoil respectively. β 1 , β 2 , β 3 in equation (7) and equation (8) are user specified coefficients while ∆Cp is the local differences between the target and computed surface pressure coefficient i.e.…”

Section: Airfoil Modifying Algorithmmentioning

confidence: 99%

An inverse approach for airfoil design

Rahmati

Aggidis

Zangeneh

2008

Advances in Fluid Mechanics VII

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Inverse design methods directly compute geometry for specified design parameters such as surface pressure or velocity, which is related to the performance of an airfoil (or a blade) geometry. These methods replace the time consuming iterative procedure of direct methods in which a large number of different blade shapes are designed and analysed to find the one which creates the surface velocity or pressure distribution closest to the desired one. In this paper a viscous inverse method for airfoil design is described. The inverse design approach computes an airfoil shape based on the target surface pressure distribution. The re-design of an airfoil, starting from an initial arbitrary profile in subsonic flow regimes, demonstrates the merits and robustness of this approach.

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“…However, when using non-linear flow-field analysis such as Navier-Stokes solvers, this iterative inverse shape design method converges slowly. A semi-analytical method for integration of such differential equations has been developed that is based on Fourier series and converges much faster [21][22][23]. This formulation will be explained for the case of inverse shape design of an isolated three-dimensional airplane wing at arbitrary flight speed.…”

Section: Elastic Membrane Motion Concept For Inverse Determination Ofmentioning

confidence: 99%

“…Notice that coordinate directions s and t are not necessarily orthogonal to each other. Evolution model of the top surface of the wing can then be assumed to be of the form [21][22][23] (2)…”

Section: Elastic Membrane Motion Concept For Inverse Determination Ofmentioning

confidence: 99%

Inverse Problems in Aerodynamics, Heat Transfer, Elasticity and Materials Design

Dulikravich¹,

Dennis²,

Baker³

et al. 2012

International Journal of Aeronautical and Space Sciences

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A number of existing and emerging concepts for formulating solution algorithms applicable to multidisciplinary inverse problems involving aerodynamics, heat conduction, elasticity, and material properties of arbitrary three-dimensional objects are briefly surveyed. Certain unique features of these algorithms and their advantages are sketched for use with boundary element and finite element methods.

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Fourier series solution for inverse design of aerodynamic shapes

Cited by 7 publications

References 3 publications

Inverse design of wind turbine blade sections for operation under icing conditions

Inverse design of wind turbine blade sections for operation under icing conditions

An inverse approach for airfoil design

Inverse Problems in Aerodynamics, Heat Transfer, Elasticity and Materials Design

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