Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section 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 Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section PDF full book. Access full book title Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by Robert F. Thompson. Download full books in PDF and EPUB format.
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Get Book Here
Book Description
This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
Author: Robert F. Thompson
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Get Book Here
Book Description
This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
Author: Boyd C. Myers
Publisher:
ISBN:
Category : Airplane
Languages : en
Pages : 36
Get Book Here
Book Description
This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Get Book Here
Book Description
Author: William C. Sleeman
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 34
Get Book Here
Book Description
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Author: Dietrich Küchemann
Publisher: AIAA Education
ISBN: 9781600869228
Category : Technology & Engineering
Languages : en
Pages : 0
Get Book Here
Book Description
Dietrich Kuchemann's The Aerodynamic Design of Aircraft is as relevant and as forward looking today as it was when it was first published in 1978. It comprises the philosophy and life's work of a unique and visionary intellect. Based upon material taught in a course at Imperial College London, the insight and intuition conveyed by this text are timeless. With its republication, Kuchemann's influence will extend to the next generation of aerospace industry students and practitioners and the vehicles they will produce. Kuchemann establishes three classes of aircraft based on the character of flow involved. Each class is suitable for a distinct cruise speed regime: classical and swept aircraft for subsonic and transonic cruise, slender-wing aircraft for supersonic cruise, and wave-rider aircraft for hypersonic cruise. Unlike most engineering texts, which focus on a set of tools, Kuchemann's approach is to focus on the problem and its solution - what kind of flow is best for a given class of aircraft and how to achieve it.With this approach, Kuchemann fully embraces the true inverse nature of design; rather than answer what flow given the shape, he strives to answer what flow given the purpose and then what shape given the flow.
Author: Robert Thomas Jones
Publisher: Princeton University Press
ISBN: 1400860776
Category : Technology & Engineering
Languages : en
Pages : 227
Get Book Here
Book Description
Originator of many of the theories used in modern wing design, Robert T. Jones surveys the aerodynamics of wings from the early theories of lift to modern theoretical developments. This work covers the behavior of wings at both low and high speeds, including the range from very low Reynolds numbers to the determination of minimum drag at supersonic speed. Emphasizing analytical techniques, Wing Theory provides invaluable physical principles and insights for advanced students, professors, and aeronautical engineers, as well as for scientists involved in computational approaches to the subject. This book is based on over forty years of theoretical and practical work performed by the author and other leading researchers in the field of aerodynamics. Originally published in 1990. 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.
Author: Hans W. Liepmann
Publisher:
ISBN:
Category :
Languages : en
Pages : 262
Get Book Here
Book Description
Author: Michael Eckert
Publisher: John Wiley & Sons
ISBN: 352761074X
Category : Science
Languages : en
Pages : 296
Get Book Here
Book Description
This is the first publication to describe the evolution of fluid dynamics as a major field in modern science and engineering. It contains a description of the interaction between applied research and application, taking as its example the history of fluid mechanics in the 20th century. The focus lies on the work of Ludwig Prandtl, founder of the aerodynamic research center (AVA) in Göttingen, whose ideas and publications have influenced modern aerodynamics and fluid mechanics in many fields. While suitable for others, this book is intended for natural scientists and engineers as well as historians of science and technology.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 766
Get Book Here
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: Hans Ulrich Meier
Publisher: Amer Inst of Aeronautics &
ISBN: 9781600867149
Category : History
Languages : en
Pages : 733
Get Book Here
Book Description
Addresses the problems and questions concerning test and measurement techniques, aerodynamics, gas dynamics, and aeroelasticity, and experience gained in developing and testing the first jet aircraft and artillery rockets with swept wings and low aspect ratio wings. This book concludes with examples of how the Allies utilized German knowledge.
