Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives 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 Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF full book. Access full book title Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13© and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives by James W. Wiggins. Download full books in PDF and EPUB format.
Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Get Book Here
Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Get Book Here
Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
![Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 [degrees] and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF](https://books.google.com/books/content/images/frontcover/5uLXSgAACAAJ?fife=w80-h100)
Author: James W. Wiggins
Publisher:
ISBN:
Category :
Languages : en
Pages : 47
Get Book Here
Book Description
Author: James W. Wiggins
Publisher:
ISBN:
Category :
Languages : en
Pages : 47
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Get Book Here
Book Description
Author: Edward Seckel
Publisher: Academic Press
ISBN: 148322015X
Category : Technology & Engineering
Languages : en
Pages : 523
Get Book Here
Book Description
Stability and Control of Airplanes and Helicopters deals with aircraft flying qualities that determine the stability and control of airplanes and helicopters. It includes problems based on real aircraft, selected to represent the gamut from simple to complicated, and from conventional utility designs to futuristic research types. Many of these problems involve comparison of theory and experiment to demonstrate their mutual relationship. Comprised of 25 chapters, this book begins with a discussion on the aerodynamics of the component parts related to the lift and moment characteristics of an airplane, including wings and associated accessories; bodies such as fuselages, nacelles, and tip tanks; and control surfaces. The reader is then introduced to some mathematical techniques for linear differential equations; steady flight at different speeds; and stick force and control-free stability. Subsequent chapters focus on flaps and high-lift devices; power and compressibility effects; and the manner in which the aircraft responds to the application of control. Aeroelasticity and longitudinal equations of motion are also examined. This monograph is intended for undergraduate and graduate students taking modern engineering courses.
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1268
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1698
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 522
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1516
Get Book Here
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
