Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds
Author: John R. Spreiter
Publisher:
Total Pages: 646
Release: 1949
Genre: Aerodynamic load
ISBN:

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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.

Aerodynamic Properties of Slender Wing-body Combinations at Subsonic, Transonic, and Supersonic Speeds

Aerodynamic Properties of Slender Wing-body Combinations at Subsonic, Transonic, and Supersonic Speeds
Author: John R. Spreiter
Publisher:
Total Pages: 33
Release: 1948
Genre: Aerodynamics
ISBN:

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It is further shown that the aerodynamic characteristics of a moderate-aspect-ratio pointed wing at sonic speed may be predictied in a manner mathematically equivalent to that used in the study of a low-aspect-ratio wing.

Index of NACA Technical Publications

Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 1370
Release: 1949
Genre: Aeronautics
ISBN:

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Tests of Two-blade Propellers in the Langley 8-foot High-speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution

Tests of Two-blade Propellers in the Langley 8-foot High-speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution
Author: James Benjamin Delano
Publisher:
Total Pages: 724
Release: 1951
Genre: Propellers, Aerial
ISBN:

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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.