Technical Note - National Advisory Committee for Aeronautics PDF Download
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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 836
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 836
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Book Description
Author: Welko E. Gasich
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 606
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Book Description
A comparison is presented between the measured take-off ground run of an airplane equipped with seven different propeller-engine gear-ratio combinations and the computed distances by two different methods.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48
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Book Description
Author: David W. Taylor Naval Ship Research and Development Center
Publisher:
ISBN:
Category : Shipbuilding
Languages : en
Pages : 90
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Book Description
Author: H. J. Hamjian
Publisher:
ISBN:
Category : Boron compounds
Languages : en
Pages : 696
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Book Description
The experiments conducted with boron carbide and each of four metals showed that nickel, cobalt, and iron formed a bonding zone between the metal and the ceramic and that chromium showed satisfactory physical wetting characteristics on the ceramic.
Author: William Arthur Nash
Publisher:
ISBN:
Category : Elastic plates and shells
Languages : en
Pages : 164
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 594
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Book Description
This document is a compilation of formulas, tables, and curves for use in the analysis of supersonic flow.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Book Description
Author: W. L. Gray
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 704
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Book Description
A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
