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At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The basic principle is the suppression of boundary layer separation by shifting the shock waves that occur on the wing toward the trailing edge and making them as weak as possible. The purpose of this report is to make available to the engineering public mathematical methods for the design of supercritical wings. These methods depend on the numerical solution of the partial differential equations of two-dimensional gas dynamics. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. Another contribution is a program for the analysis of transonic flow with shocks past an airfoil at off-design conditions. In our design work we include a turbulent boundary layer correction. Part I of the paper is devoted to a description of the mathemati- cal theory and need not be studied by those primarily concerned with running the programs. Part II is a manual for users of our programs which is independent of the theoretical part. In Part III and in Appendices II and III we give numerical examples and discuss computa- tional results. The main substance of the report, however, is contained in the listing of the computer programs themselves in Appendix IV. We have used the Fortran language throughout and we have included numerous comment cards in the listing.
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A Theory of Supercritical Wing Sections. (= Lecture Notes in Economics and Mathematical Systems, Band 66).
Edité par
Springer, Berlin, 1972, 1972
ISBN 10 : 3540058079
ISBN 13 : 9783540058076
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8° , Softcover/Paperback. 1.Auflage,. IV, 211 Seiten Einband etwas berieben, Bibl.Ex., innen guter und sauberer Zustand 9783540058076 Sprache: Englisch Gewicht in Gramm: 460. N° de réf. du vendeur 143059
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples (Lecture Notes in Economics and Mathematical Systems 66)
Edité par
Springer, 1972
ISBN 10 : 3540058079
ISBN 13 : 9783540058076
Ancien ou d'occasion
Couverture rigide
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Hard Cover. Etat : Good. No Jacket. Ex-library with the usual features. The interior is clean and tight. Binding and cover are good. The book has been rebound in a hard cover library binding. 211 pages. Ex-Library. N° de réf. du vendeur 033407sf
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples
Edité par
Springer Berlin Heidelberg Apr 1972, 1972
ISBN 10 : 3540058079
ISBN 13 : 9783540058076
Neuf
Taschenbuch
Vendeur : BuchWeltWeit Ludwig Meier e.K., Bergisch Gladbach, Allemagne
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Taschenbuch. Etat : Neu. This item is printed on demand - it takes 3-4 days longer - Neuware -At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The basic principle is the suppression of boundary layer separation by shifting the shock waves that occur on the wing toward the trailing edge and making them as weak as possible. The purpose of this report is to make available to the engineering public mathematical methods for the design of supercritical wings. These methods depend on the numerical solution of the partial differential equations of two-dimensional gas dynamics. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. Another contribution is a program for the analysis of transonic flow with shocks past an airfoil at off-design conditions. In our design work we include a turbulent boundary layer correction. Part I of the paper is devoted to a description of the mathemati cal theory and need not be studied by those primarily concerned with running the programs. Part II is a manual for users of our programs which is independent of the theoretical part. In Part III and in Appendices II and III we give numerical examples and discuss computa tional results. The main substance of the report, however, is contained in the listing of the computer programs themselves in Appendix IV. We have used the Fortran language throughout and we have included numerous comment cards in the listing. 220 pp. Englisch. N° de réf. du vendeur 9783540058076
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples (Paperback)
Edité par
Springer-Verlag Berlin and Heidelberg GmbH & Co. KG, Berlin, 1972
ISBN 10 : 3540058079
ISBN 13 : 9783540058076
Neuf
Paperback
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Paperback. Etat : new. Paperback. At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The basic principle is the suppression of boundary layer separation by shifting the shock waves that occur on the wing toward the trailing edge and making them as weak as possible. The purpose of this report is to make available to the engineering public mathematical methods for the design of supercritical wings. These methods depend on the numerical solution of the partial differential equations of two-dimensional gas dynamics. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. Another contribution is a program for the analysis of transonic flow with shocks past an airfoil at off-design conditions. In our design work we include a turbulent boundary layer correction. Part I of the paper is devoted to a description of the mathemati cal theory and need not be studied by those primarily concerned with running the programs. Part II is a manual for users of our programs which is independent of the theoretical part. In Part III and in Appendices II and III we give numerical examples and discuss computa tional results. The main substance of the report, however, is contained in the listing of the computer programs themselves in Appendix IV. We have used the Fortran language throughout and we have included numerous comment cards in the listing. At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. Shipping may be from multiple locations in the US or from the UK, depending on stock availability. N° de réf. du vendeur 9783540058076
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples: With Computer Programs and Examples (Lecture Notes in Economics and Mathematical Systems, 66)
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples: With Computer Programs and Examples (Lecture Notes in Economics and Mathematical Systems, 66)
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples
Edité par
Springer Berlin Heidelberg, 1972
ISBN 10 : 3540058079
ISBN 13 : 9783540058076
Neuf
Couverture souple
Vendeur : moluna, Greven, Allemagne
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Etat : New. Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The basic principle is the suppression of boundary layer separation by shifting the shock waves that occur o. N° de réf. du vendeur 4878946
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples
Vendeur : Books Puddle, New York, NY, Etats-Unis
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Etat : New. pp. 220. N° de réf. du vendeur 2658580428
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples
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Etat : New. Print on Demand pp. 220 19 Figures, 66:B&W 7 x 10 in or 254 x 178 mm Perfect Bound on White w/Gloss Lam. N° de réf. du vendeur 51012115
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A Theory of Supercritical Wing Sections, with Computer Programs and Examples
impression à la demandeVendeur : Biblios, Frankfurt am main, HESSE, Allemagne
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Etat : New. PRINT ON DEMAND pp. 220. N° de réf. du vendeur 1858580422
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