Aerodynamic Loads at Mach Numbers from 0.70 to 2.22 on an Airplane Model Having a Wing and Canard of Triangular Plan Form and Either Single Or Twin Vertical Tails PDF Download
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Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 64
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Book Description
Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 64
Get Book Here
Book Description
Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 1
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Book Description
Results of an investigation of the aerodynamic loads on a canard airplane model are presented without detailed analysis for the Mach number range of 0.70 to 2.22. The model consisted of a triangular wing and canard of aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and either a single body-mounted vertical tail or twin wing-mounted vertical tails of low aspect ratio and sweptback plan form. The body, right wing panel, single vertical tail, and left twin vertical tail were instrumented for measuring pressures. Data were obtained for angles of attack ranging from -4 degrees to +16 degrees, nominal canard deflection angles of 0 degrees and 10 degrees, and angles of sideslip of 0 degrees and 5.3 degrees. The Reynolds number was 2.9 x 10 to the 6th power based on the wing mean aerodynamic chord. (Author).
Author: Victor L. Peterson
Publisher:
ISBN:
Category :
Languages : en
Pages : 57
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Book Description
Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 336
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
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Book Description
Author: Robert C. Nelson
Publisher: WCB/McGraw-Hill
ISBN: 9780071158381
Category : Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite
Languages : en
Pages : 441
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Book Description
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Author: Edward J. Ray
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author: Richard T. Whitcomb
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 12
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Book Description
Summary: Data are presented to show the changes that occur in the spanwise load distributions on wings when the critical Mach number is exceeded. These data indicate that the magnitude of the changes in spanwise load distribution varies with the magnitude of the spanwise variation in the critical Mach numbers of the sections. Means of reducing the magnitudes of such changes are considered.
Author: John P.. Mugler
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
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Book Description
Author: George H. Holdaway
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82
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Book Description
