Experience with Transonic Unsteady Aerodynamic Calculations PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 26
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Author:
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ISBN:
Category :
Languages : en
Pages : 16
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Author: Ülgen Gülçat
Publisher: Springer Science & Business Media
ISBN: 3642147615
Category : Technology & Engineering
Languages : en
Pages : 348
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Book Description
In this textbook, the author introduces the concept of unsteady aerodynamics and its underlying principles. He provides the readers with a full review of fundamental physics of the free and the forced unsteadines, the terminology and basic equations of aerodynamics ranging from incompressible flow to hypersonics. The book also covers the modern topics concerning the developments made during the last years, especially in relation to wing flappings for propulsion. The book is written for graduate and senior year undergraduate students in Aerodynamics, and it serves as a reference for experienced researchers. Each chapter includes ample examples, questions, problems and relevant references.
Author: David Nixon
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 410
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Book Description
This volume complements Transonic aerodynamics (v.81 in the series) which is concerned with steady flow. This is the only book to address the subject of unsteady transonic aerodynamics, a field much different from steady aerodynamics. The most pronounced difference is the complex shock wave motions
Author:
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ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 684
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Author:
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ISBN:
Category :
Languages : en
Pages : 38
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Author:
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ISBN:
Category :
Languages : en
Pages : 14
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Author: S. Y. Ruo
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 60
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Book Description
An analytical approach is presented to account for some of the nonlinear characteristics of the transonic flow equation for finite thickness wings undergoing harmonic oscillation at sonic flight speed in an inviscid, shock-free fluid. The thickness effect is accounted for in the analysis through use of the steady local Mach number distribution over the wing at its mean position by employing the local linearization concept and a coordinate transformation. Computed results are compared with that of the linearized theory and experiments. Based on the local linearization concept, an alternate formulation avoiding the limitations of the coordinate transformation method is presented.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Author:
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ISBN:
Category :
Languages : en
Pages : 30
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