Effects of a Pointed Nose on Spin Characteristics of a Fighter Airplane Model Including Correlation with Theoretical Calculations
Author: Joseph R. Chambers
Publisher:
Published: 1970
Total Pages: 68
ISBN-13:
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Author: Joseph R. Chambers
Publisher:
Published: 1970
Total Pages: 68
ISBN-13:
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Publisher:
Published: 1970
Total Pages: 1730
ISBN-13:
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Publisher:
Published: 1971
Total Pages: 580
ISBN-13:
DOWNLOAD EBOOKA selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author: United States. Superintendent of Documents
Publisher:
Published: 1979
Total Pages: 1504
ISBN-13:
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Publisher:
Published: 1972
Total Pages: 320
ISBN-13:
DOWNLOAD EBOOKAuthor: United States. Superintendent of Documents
Publisher:
Published: 1966
Total Pages: 1464
ISBN-13:
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Publisher:
Published: 1972
Total Pages: 300
ISBN-13:
DOWNLOAD EBOOKAuthor: Robert F. Stengel
Publisher: Princeton University Press
Published: 2022-11-01
Total Pages: 912
ISBN-13: 0691220255
DOWNLOAD EBOOKAn updated and expanded new edition of an authoritative book on flight dynamics and control system design for all types of current and future fixed-wing aircraft Since it was first published, Flight Dynamics has offered a new approach to the science and mathematics of aircraft flight, unifying principles of aeronautics with contemporary systems analysis. Now updated and expanded, this authoritative book by award-winning aeronautics engineer Robert Stengel presents traditional material in the context of modern computational tools and multivariable methods. Special attention is devoted to models and techniques for analysis, simulation, evaluation of flying qualities, and robust control system design. Using common notation and not assuming a strong background in aeronautics, Flight Dynamics will engage a wide variety of readers, including aircraft designers, flight test engineers, researchers, instructors, and students. It introduces principles, derivations, and equations of flight dynamics as well as methods of flight control design with frequent reference to MATLAB functions and examples. Topics include aerodynamics, propulsion, structures, flying qualities, flight control, and the atmospheric and gravitational environment. The second edition of Flight Dynamics features up-to-date examples; a new chapter on control law design for digital fly-by-wire systems; new material on propulsion, aerodynamics of control surfaces, and aeroelastic control; many more illustrations; and text boxes that introduce general mathematical concepts. Features a fluid, progressive presentation that aids informal and self-directed studyProvides a clear, consistent notation that supports understanding, from elementary to complicated conceptsOffers a comprehensive blend of aerodynamics, dynamics, and controlPresents a unified introduction of control system design, from basics to complex methodsIncludes links to online MATLAB software written by the author that supports the material covered in the book
Author: Sue B. Grafton
Publisher:
Published: 1971
Total Pages: 44
ISBN-13:
DOWNLOAD EBOOKA low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -10 [degree] to 110 [degree] for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to determine the effects of these variables on the stability derivatives. The effect of the vertical and horizontal tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very high angles of attack associated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives.