Aerodynamic shape inverse design using a Fourier series method

Dulikravich, George S.; Baker, Daniel P.

doi:10.2514/6.1999-185

Cited by 24 publications

(11 citation statements)

References 4 publications

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“…The inverse design, following the elastic membrane technique using Fourier series, showed to be e cient ÿnding new aerodynamical geometries for given pressure coe cient di erences. The Fourier series method does not require modiÿcation of the ow-ÿeld analysis software, converges fast because of its analytical expressions and maintains this behaviour when increasing ow ÿeld non-linearities [9].…”

Section: Discussionmentioning

confidence: 99%

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Euler solutions for aerodynamic inverse shape design

Bortoli

Quadros

2003

Numerical Methods in Fluids

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SUMMARYContributions to the aerodynamics development have to be involved to achieve an increase in quality, reducing time and computer costs. Therefore, this work develops an optimization method based on the ÿnite volume explicit Runge-Kutta multi-stage scheme with central spatial discretization in combination with multigrid and preconditioning. The multigrid approach includes local time-stepping and residual smoothing. Such a method allows getting the goal of compressible and almost incompressible solution of uid ows, having a rate of convergence almost independent from the Mach number. Numerical tests are carried out for the NACA 0012 and 0009 airfoils and three-dimensional wings based on NACA proÿles for Mach-numbers ranging from 0.8 to 0.002 using the Euler equations. These calculations are found to compare favorably with experimental and numerical data available in the literature. Besides, it is worth pointing out that these results build on earlier ones when ÿnding appropriate new three-dimensional aerodynamical geometries.

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Section: Discussionmentioning

confidence: 99%

“…To the shape evolution, using the elastic membrane technique [8,9], one separates the upper and lower sides of the airfoil (wing cross-section). On the upper side the Fourier serie results…”

Section: Inverse Shape Designmentioning

confidence: 99%

Euler solutions for aerodynamic inverse shape design

Bortoli

Quadros

2003

Numerical Methods in Fluids

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“…In the last two decades, three-dimensional inverse design methods have emerged and been applied successfully for a wide range of designs, involving both radial/mixed flow turbomachinery blades and wings (Zangeneh, 1991;Demeulenaere & Van Den Braembussche, 1996;Dulikravich & Baker, 1999). Quite a new approach to the 3D design of axial compressor bladings has been recently proposed by Tiow, 2002.…”

Section: Inverse Methodsmentioning

confidence: 99%

Advances in Aerodynamic Design of Gas Turbines Compressors

Benini¹

2010

Gas Turbines

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“…However, the main point to note is that the second order spanwise derivative term is also second order small in the flow direction deviation from chordwise, but the cross-term is first order so much stronger. Earlier models such as, 8 relying on e.g. a membrane analogue, have no cross derivatives but substantial spanwise second derivatives.…”

Section: E Influence Of Cross-flow*mentioning

confidence: 99%

Hybrid feedback design for subsonic and transonic airfoils and wings

Zhang

Rizzi

Nangia

2014

52nd Aerospace Sciences Meeting

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A hybrid inverse/optimization method for subsonic/transonic airfoil and wing shape design is presented with application to a range of airfoil and wing cases, in preparation for the test cases defined for the Special Session of SciTech 2014. The method is hybrid in the sense that it combines the traditional inverse design technique with an optimization procedure that determines the optimum target pressure distribution. This paper emphasizes the first part, the development of SCID, the Surface Curvature Inverse Design method, the theory upon which it is based, including many of the details involved with shocks, smoothing and cross flow. The application of SCID to wing design poses many challenges, and how they are met is discussed in the context of a number of inverse design test cases for airfoils and wings. The procedure works well for airfoils, whereas twist optimization for transonic wings remains a challenge. The real benchmarks for our hybrid approach are the three Optimization Discussion Group design problems. Solutions are presented for the drag minimization of the NACA airfoil along with the wing twist optimization problem, and conclusions are drawn from the results obtained. Work has started on the drag minimization of the CRM wing in transonic flight, and final results will be presented in a future paper.

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Aerodynamic shape inverse design using a Fourier series method

Cited by 24 publications

References 4 publications

Euler solutions for aerodynamic inverse shape design

Euler solutions for aerodynamic inverse shape design

Advances in Aerodynamic Design of Gas Turbines Compressors

Hybrid feedback design for subsonic and transonic airfoils and wings

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