Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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.
Aerodynamic Properties of Cruciform-wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds
Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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.
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 646
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.
Bibliography of Technical Reports
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 62
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 62
Book Description
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 654
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 654
Book Description
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:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 724
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.
Publisher:
ISBN:
Category : Propellers, Aerial
Languages : en
Pages : 724
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.
Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 18
Book Description
Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 996
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 996
Book Description
Annual Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Technical Note
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 370
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 370
Book Description
NASA Technical Memorandum
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 146
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 146
Book Description
Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Author: James C. Sivells
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 722
Book Description
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.
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 722
Book Description
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.