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:

Published: 1949

Total Pages: 646

ISBN-13:

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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.

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:

Published: 1951

Total Pages: 724

ISBN-13:

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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.

Report
Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1957

Total Pages: 18

ISBN-13:

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Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data

Author: James C. Sivells

Publisher:

Published: 1951

Total Pages: 722

ISBN-13:

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A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.