The choice of the system of geometric parameters of an optimized wing

Takovitskii, S. A.

doi:10.1016/s0021-8928(98)00097-5

Cited by 4 publications

(6 citation statements)

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“…The result obtained is consistent with the data from the numerical investigation in Ref. 12, where the conclusion was drawn that it is possible to achieve high aerodynamic characteristics in a class of wings composed of four flat elements.…”

Section: The Ratio Of the Drag Coefficients Of The Deformed And Flat supporting

confidence: 90%

“…The results obtained are in complete agreement with the data from the previously performed investigations. 12,13 Nevertheless, representing the wing by a hypergeometric directrix reduces the number of geometrical parameters to the greatest extent.…”

Section: The Ratio Of the Drag Coefficients Of The Deformed And Flat mentioning

confidence: 99%

“…An alternative procedure is to represent the wing by a set of triangular elements joined along rays from the apex of the wing. 12 Successive reduction of the size of the elements enables one to investigate the nature of the variation of the aerodynamic drag and to find the simplest deformations. According to the assumptions of the linear theory, infinite pressure values appear on the wing surface, complicating the applicability and reducing the accuracy of numerical methods of investigation.…”

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confidence: 99%

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The conical deformation of a delta wing with sonic leading edges

Takovitskii¹

2014

Journal of Applied Mathematics and Mechanics

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Section: The Ratio Of the Drag Coefficients Of The Deformed And Flat supporting

confidence: 90%

Section: The Ratio Of the Drag Coefficients Of The Deformed And Flat mentioning

confidence: 99%

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confidence: 99%

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The conical deformation of a delta wing with sonic leading edges

Takovitskii¹

2014

Journal of Applied Mathematics and Mechanics

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“…This approach enables to investigate the variation of the drag as the shape of the wing is made more complicated. 7 The aerodynamic feature of the wing is constancy of the gas-dynamic functions along the rays.…”

Section: Optimization Problem Statementmentioning

confidence: 99%

“…7 For example, at Mach number M=2 the eigenvalues of the objective function Hessian matrix differ more than by 100 times, and the value of the asymptotic error parameter gets close to unit. In this case at arbitrary choice of the geometrical parameters the reliable solution of the problem is not guaranteed.…”

Section: Optimization Problem Statementmentioning

confidence: 99%

High-speed flying vehicle with hypergeometrically shaped windward aerodynamic surface

Takovitskii¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This work discusses the problem of reducing the drag due to lift at high-speed flight conditions. To accelerate the optimization algorithm convergence and to study characteristic features of the optimal delta wing the procedure of the geometry parameters system selection is developed within the framework of the linear theory. It is established that the hypergeometrical directrix of the wing describes near to optimum aerodynamic shape and corresponds to a superelliptical distribution of the local angle of attack over the wing span. Differences between the results of the theoretical studying and the direct numerical optimization based on the Euler's equations are analyzed. Configuration of the high-speed flying vehicle, designed under HEXAFLY-INT project, with hypergeometrically profiled windward surface is proposed to enhance aerodynamic performance. Flow fields and aerodynamic loads numerical studying is carried out in a wide range of the Mach number. Nomenclature X = axis directed along the free stream R  = aerodynamic force velocity 2 n  = nozzle exit normal Y = axis of lift force I = flow momentum Z = lateral axis y = normalized normal coordinate M = Mach number z = normalized lateral coordinate V = free stream velocity Re = Reynolds number α = angle of attack C P = pressure coefficient N = number of elements q = pressure velocity F = objective function G = constraint function Subscripts C D = aerodynamic drag coefficient fl = flat wing C L = lift coefficient EXT = external C m = pitching moment coefficient f = mass flow rate ν = eigenvalue u = eigenvector H = Hessian matrix n = relative sweepback μ = Mach angle χ = sweep angle at the leading edge φ = perturbation velocity potential λ = Lagrange multiplier E = form parameter 2 F 1 = Gauss hypergeometric function ψ = twist angle L = fuselage length S = reference area 1 Head of Research Group, Aerodynamics Department, TsAGI, c.a.t@tsagi.ru, not a member of the AIAA Downloaded by UNIVERSITY OF ILLINOIS on October 1, 2015 | http://arc.aiaa.org |

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The optimal conical twist of a delta wing

Takovitskii

2012

Journal of Applied Mathematics and Mechanics

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The choice of the system of geometric parameters of an optimized wing

Cited by 4 publications

References 1 publication

The conical deformation of a delta wing with sonic leading edges

The conical deformation of a delta wing with sonic leading edges

High-speed flying vehicle with hypergeometrically shaped windward aerodynamic surface

The optimal conical twist of a delta wing

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