Experimental Verification of the Rudder-free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction 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 Experimental Verification of the Rudder-free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction PDF full book. Access full book title Experimental Verification of the Rudder-free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction by Marion O. McKinney. Download full books in PDF and EPUB format.
Author: Marion O. McKinney
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 70
Get Book
Book Description
When this assumption is made that the rolling motions alone or the lateral and rolling motions may be neglected in the calculations of rudder-free stability, it is possible to predict satisfactorily the characteristics of the long-period (Dutch roll type) rudder-free oscillation for airplanes only when the effective-dihedral angle is small. With these simplifying assumptions, however, satisfactory prediction of the short-period oscillation may be obtained for any dihedral. Further simplification of the theory based on the assumption that the rudder moment of inertia might be disregarded was found to be invalid because this assumption made it impossible to calculate the characteristics of the short-period oscillations.
Author: Marion O. McKinney
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 70
Get Book
Book Description
When this assumption is made that the rolling motions alone or the lateral and rolling motions may be neglected in the calculations of rudder-free stability, it is possible to predict satisfactorily the characteristics of the long-period (Dutch roll type) rudder-free oscillation for airplanes only when the effective-dihedral angle is small. With these simplifying assumptions, however, satisfactory prediction of the short-period oscillation may be obtained for any dihedral. Further simplification of the theory based on the assumption that the rudder moment of inertia might be disregarded was found to be invalid because this assumption made it impossible to calculate the characteristics of the short-period oscillations.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 298
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 762
Get Book
Book Description
Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 32
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1370
Get Book
Book Description
Author: Arthur Earl Bryson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 340
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1172
Get Book
Book Description
Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 592
Get Book
Book Description
Calculations of the rotational-noise and vortex noise loudness levels at distances of 300 and 1000 feet have been made for a large number of propellers in forward flight of 50 to 200 miles per hour and for engine ratings of 100 to 300 horsepower. Propellers of two, four, six, and eight blades, diameters of 6, 8, and 10 feet, and rotational speeds of 1000 to 2000 rpm are considered. Calculated results are presented in chart form for convenience of designers of propellers for applications in which loudness is an important consideration.
