Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 87
Book Description
The work presents the design considerations and the calibration of a shock tunnel for aerodynamic measurements at hypersonic Mach numbers. The shock tunnel is composed of a shock tube which is used for the production of high temperature and high pressure air reservoir, which is then expanded through a supersonic nozzle, thereby attaining high Mach number flow in the test section. In order to obtain maximum test time a 'tailored' mode of operation is used for this shock tunnel. A method for calculating the optimum ratio of the compression Chamber length to the low pressure tube length for a given total shock tube length that will result in a maximum test duration is presented. The flow in the test section is calibrated using a total pressure rake and by static pressure measurements and measurements of stagnation point heat transfer rates at various points in the test section. The flow conditions are then calculated using the theoretical relations for stagnation point heat transfer rates. The experimental results show the flow in the horizontal plane with a relatively thin boundary layer.
Calibration of the Tailored Interface 8 Inches X 10 Inches Shock Tunnel
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 87
Book Description
The work presents the design considerations and the calibration of a shock tunnel for aerodynamic measurements at hypersonic Mach numbers. The shock tunnel is composed of a shock tube which is used for the production of high temperature and high pressure air reservoir, which is then expanded through a supersonic nozzle, thereby attaining high Mach number flow in the test section. In order to obtain maximum test time a 'tailored' mode of operation is used for this shock tunnel. A method for calculating the optimum ratio of the compression Chamber length to the low pressure tube length for a given total shock tube length that will result in a maximum test duration is presented. The flow in the test section is calibrated using a total pressure rake and by static pressure measurements and measurements of stagnation point heat transfer rates at various points in the test section. The flow conditions are then calculated using the theoretical relations for stagnation point heat transfer rates. The experimental results show the flow in the horizontal plane with a relatively thin boundary layer.
Publisher:
ISBN:
Category :
Languages : en
Pages : 87
Book Description
The work presents the design considerations and the calibration of a shock tunnel for aerodynamic measurements at hypersonic Mach numbers. The shock tunnel is composed of a shock tube which is used for the production of high temperature and high pressure air reservoir, which is then expanded through a supersonic nozzle, thereby attaining high Mach number flow in the test section. In order to obtain maximum test time a 'tailored' mode of operation is used for this shock tunnel. A method for calculating the optimum ratio of the compression Chamber length to the low pressure tube length for a given total shock tube length that will result in a maximum test duration is presented. The flow in the test section is calibrated using a total pressure rake and by static pressure measurements and measurements of stagnation point heat transfer rates at various points in the test section. The flow conditions are then calculated using the theoretical relations for stagnation point heat transfer rates. The experimental results show the flow in the horizontal plane with a relatively thin boundary layer.
Calibration of the Tailored Interface 8" X 10" Shock Tunnel
Author: A. Kuritzky
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 564
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 564
Book Description
Aerodynamic Characteristics of a Large-angle Blunt Cone with and Without Fence-type Afterbodies
Author: Kenneth W. McAlister
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 60
Book Description
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 60
Book Description
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
Book Description
Government Reports Index
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 716
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 716
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1096
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1096
Book Description
Hypersonic Shock Tunnel
Author: Cornell Aeronautical Laboratory. Experimental Facilities Division
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Book Description
The High Temperature Aspects of Hypersonic Flow
Author: Wilbur C. Nelson
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
Book Description
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
Book Description
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Government Reports Announcements
Author:
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1910
Book Description
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1910
Book Description