Linearized Lifting Surface Theory For Swept Back Wings With Slender Plan Forms

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Linearized Lifting Surface Theory For Swept Back Wings With Slender Plan Forms

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Author : Harvard Lomax
language : en
Publisher:
Release Date : 1949

Linearized Lifting Surface Theory For Swept Back Wings With Slender Plan Forms written by Harvard Lomax and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerodynamic load categories.

The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.

Linearized Theory Of Steady High Speed Flow

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Author :
language : en
Publisher: CUP Archive
Release Date :

Linearized Theory Of Steady High Speed Flow written by and has been published by CUP Archive this book supported file pdf, txt, epub, kindle and other format this book has been release on with categories.

Linearized Theory Of Steady High Speed Flow

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Author : G. N. Ward
language : en
Publisher: Cambridge University Press
Release Date : 2016-02-25

Linearized Theory Of Steady High Speed Flow written by G. N. Ward and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2016-02-25 with Mathematics categories.

Originally published in 1955, this book is devoted exclusively to the problems involved in solving the non-linear equations of motion for compressible fluids.

Technical Note National Advisory Committee For Aeronautics

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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1958

Technical Note National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1958 with Aeronautics categories.

Mechanical And Corrosion Tests Of Spot Welded Aluminum Alloys

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Author : Fred M. Reinhart
language : en
Publisher:
Release Date : 1951

Mechanical And Corrosion Tests Of Spot Welded Aluminum Alloys written by Fred M. Reinhart and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aluminum alloys categories.

Corrosion behaviro of spot-welded aluminum-alloy (alclad 24S-T3, 24S-T3, alclade XB75S-T6, XB75S-T6, and R-301-T6) panels of varying weld quality was determined. Tidewater and weather exposure tests were made and the results were evaluated largely in terms of distribution of corrosion products and effects on weld strength. Metallographic examinations of several of the alloys were also made to determine the extent and type of corrosion attack associated with various welding and exposure conditions.

Aero Digest

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Author :
language : en
Publisher:
Release Date : 1950

Aero Digest written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Aeronautics categories.

Nasa Technical Memorandum

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Author :
language : en
Publisher:
Release Date : 1971

Nasa Technical Memorandum written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Aeronautics categories.

Method For Calculating Lift Distribtutions For Unswept Wings With Flaps Or Ailerons By Use Of Nonlinear Section Lift Data

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Author : James C. Sivells
language : en
Publisher:
Release Date : 1951

Method For Calculating Lift Distribtutions For Unswept Wings With Flaps Or Ailerons By Use Of Nonlinear Section Lift Data written by James C. Sivells and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Ailerons categories.

A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.

Applied Mechanics Reviews

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Author :
language : en
Publisher:
Release Date : 1950

Applied Mechanics Reviews written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Mechanics, Applied categories.

Aerodynamic Components Of Aircraft At High Speeds

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Author : Allen F. Donovan
language : en
Publisher: Princeton University Press
Release Date : 2015-12-08

Aerodynamic Components Of Aircraft At High Speeds written by Allen F. Donovan and has been published by Princeton University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-12-08 with Science categories.

Volume VII of the High Speed Aerodynamics and Jet Propulsion series. It deals with applications to specific components of the complete aircraft. Sections of the volume include: aerodynamics of wings at high speed, aerodynamics of bodies at high speed, interaction problems, propellers at high speed, diffusers and nozzles, and nonsteady wing characteristics. Originally published in 1957. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.