Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds PDF Download
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Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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Book Description
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: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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Book Description
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: Harvard Lomax
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 38
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Book Description
The damping-in-roll parameter C(iota)(p) is calculated theoretically for triangular wings on cylindrical bodies and for a class of wings with sweptback plan forms. The analysis is based on the usual assumptions of linearized compressible-flow theory together with the added restrictions that at the free-stream Mach number M(omicron) the product of lM(omicron)(2) and the streamwise velocity gradient is small.
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 : 548
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 694
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Author: John P. Gapcynski
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1078
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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 : 664
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Author: James Benjamin Delano
Publisher:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 724
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Book Description
This paper presents propeller characteristics for two propellers that differ only in inboard pitch distribution. The forward Mach number range extended to 0.062 and the blade-angle range was from 20 to 55 degrees. Section thrust-coefficient data are also presented to afford a more detailed analysis of the effects of modifying the pitch distribution of the inboard sections of a propeller.
