A Study of the Problem of Designing Airplanes with Satisfactory Inherent Damping of the Dutch Roll Oscillation PDF Download
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Author: Anatol Roshko
Publisher:
ISBN:
Category : Aerial spraying and dusting in agriculture
Languages : en
Pages : 258
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Book Description
Author: Anatol Roshko
Publisher:
ISBN:
Category : Aerial spraying and dusting in agriculture
Languages : en
Pages : 258
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 900
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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.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1066
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Book Description
Author: Edward Seckel
Publisher: Academic Press
ISBN: 148322015X
Category : Technology & Engineering
Languages : en
Pages : 523
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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:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 616
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 50
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Book Description
Author: Clarence L. Gillis
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48
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Book Description
A test and analysis method is presented for determining airplane lateral stability characteristics, including aerodynamic derivatives, from flight tests of scale models. The method of analysis utilizes the rotating time-vector concept and also a quasi-static approach. Data are presented at transonic speeds for three swept-wing rocket-propelled models differing only in vertical position and dihedral of the wing. The method proved to be adequate for delineating the major effects of the geometric variations on the aerodynamic lateral stability derivatives. The effects of Reynolds number on the linearity of the static stability data for an unswept wing configuration are illustrated.
