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Author: Elie Carafoli
Publisher: Elsevier
ISBN: 1483160270
Category : Technology & Engineering
Languages : en
Pages : 611
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Book Description
Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Author: Elie Carafoli
Publisher: Elsevier
ISBN: 1483160270
Category : Technology & Engineering
Languages : en
Pages : 611
Get Book Here
Book Description
Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.
Author: Clarence A. Syvertson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 304
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Book Description
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
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Book Description
Author: Arthur W. Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 454
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Book Description
![Hypersonic Dynamic Stability: Summary [by] L. A. Marshall PDF](https://books.google.com/books/content/images/frontcover/YMxPAAAAYAAJ?fife=w80-h100)
Author: General Electric Company
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
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Book Description
Author: Davis H. Crawford
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 680
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Book Description
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 1416
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 394
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Book Description
