Towing Tests of Models as an Aid in the Design of Seaplanes PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Towing Tests of Models as an Aid in the Design of Seaplanes PDF full book. Access full book title Towing Tests of Models as an Aid in the Design of Seaplanes by P. Schröder. Download full books in PDF and EPUB format.
Author: P. Schröder
Publisher:
ISBN:
Category : Marine towing
Languages : en
Pages : 664
Get Book Here
Book Description
This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
Author: P. Schröder
Publisher:
ISBN:
Category : Marine towing
Languages : en
Pages : 664
Get Book Here
Book Description
This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 790
Get Book Here
Book Description
Chiefly translations from foreign aeronautical journals.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 332
Get Book Here
Book Description
Chiefly translations from foreign aeronautical journals.
Author: H. Weinhart
Publisher:
ISBN:
Category : Automobiles
Languages : en
Pages : 574
Get Book Here
Book Description
Engine knock is, as is known, preceded by normal burning of the first part of the charge, and only the part burned last (residual charge), knocks. The aim of the present measurements was, first, to reexamine the combustion form in this residual charge, because of the absence of uniform and frequently contradictory results in the very extensive literature on the subject. On top of that, an attempt was to be made to gain a deeper insight into the mechanism accompanying the combustion process, by means of the electrical test equipment perfected in recent years.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 312
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 760
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 660
Get Book Here
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: J. A. Spanogle
Publisher:
ISBN:
Category : Combustion chambers
Languages : en
Pages : 562
Get Book Here
Book Description
A gas-sampling valve of the inertia-operated type has been designed for procuring samples of the gases in the combustion chamber of internal-combustion engines at identical points in successive cycles so that the analysis of the gas samples thus procured may aid in the study of the process of combustion.
Author: J. Stuper
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 720
Get Book Here
Book Description
Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
