The Tailored Interface Hypersonic Shock Tunnel PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download The Tailored Interface Hypersonic Shock Tunnel PDF full book. Access full book title The Tailored Interface Hypersonic Shock Tunnel by H. S. Glick. Download full books in PDF and EPUB format.
Author: H. S. Glick
Publisher:
ISBN:
Category :
Languages : en
Pages : 7
Get Book Here
Book Description
Author: H. S. Glick
Publisher:
ISBN:
Category :
Languages : en
Pages : 7
Get Book Here
Book Description
Author: Roy B. Phillips
Publisher:
ISBN:
Category : Shock tubes
Languages : en
Pages : 126
Get Book Here
Book Description
Author: Michael Peter Wood
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 118
Get Book Here
Book Description
Author: Raymond Leroy Enlow
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 150
Get Book Here
Book Description
Author: Cornell Aeronautical Laboratory. Experimental Facilities Division
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Get Book Here
Book Description
Author: Cornell Aeronautical Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 46
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 87
Get Book Here
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.
Author: M. P. Wood
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Get Book Here
Book Description
