A Theoretical Study of the Aerodynamics of Slender Cruciform-wing Arrangements and Their Wakes
Author : John R. Spreiter
Publisher :
Page : pages
File Size : 35,9 MB
Release : 1957
Category :
ISBN :
Author : John R. Spreiter
Publisher :
Page : pages
File Size : 35,9 MB
Release : 1957
Category :
ISBN :
Author : United States. National Advisory Committee for Aeronautics
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Page : 28 pages
File Size : 47,37 MB
Release : 1957
Category : Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
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Page : 1216 pages
File Size : 49,47 MB
Release : 1958
Category : Aeronautics
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Author :
Publisher :
Page : 900 pages
File Size : 42,36 MB
Release : 1957
Category : Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 388 pages
File Size : 23,54 MB
Release : 1959
Category : Aeronautics
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Author :
Publisher :
Page : 818 pages
File Size : 20,72 MB
Release : 1954
Category : Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
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Page : 534 pages
File Size : 20,59 MB
Release : 1953
Category : Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : pages
File Size : 40,36 MB
Release : 1957
Category : Aeronautics
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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author : John R. Spreiter
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Page : 646 pages
File Size : 28,13 MB
Release : 1949
Category : Aerodynamic load
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The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.
Author : Ralph T. Dittrich
Publisher :
Page : 690 pages
File Size : 29,77 MB
Release : 1956
Category : Combustion chambers
ISBN :
An experimental investigation was conducted to determine the effects of various geometric and flow factors on the discharge coefficients for circular holes having flow parallel to the plane of the hole. The geometric and flow factors considered were hole diameter, wall thickness at the hole, parallel-fllow duct height, boundary-layer thickness, parallel-flow velocity, static-pressure level, and pressure ratio across the test hole.