The Design of a Small Supersonic Wind-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 Design of a Small Supersonic Wind-tunnel PDF full book. Access full book title The Design of a Small Supersonic Wind-tunnel by Gary Arnold Flandro. Download full books in PDF and EPUB format.
Author: Gary Arnold Flandro
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Get Book Here
Book Description
Author: Gary Arnold Flandro
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Get Book Here
Book Description
Author: Thomas G. Piercy
Publisher:
ISBN:
Category :
Languages : en
Pages : 266
Get Book Here
Book Description
Author: Peter Ashurkoff
Publisher:
ISBN:
Category :
Languages : en
Pages : 170
Get Book Here
Book Description
Author: F. Richard Folkerth
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 178
Get Book Here
Book Description
Author: Robin Allan Bithell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 212
Get Book Here
Book Description
Author: Rudolf Hermann
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 90
Get Book Here
Book Description
In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Author: George M. Stokes
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 60
Get Book Here
Book Description
Author: William McKinley Davis
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 66
Get Book Here
Book Description
Author: Wendell Davis
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
Author: Myles Barton Mitchell
Publisher:
ISBN:
Category :
Languages : en
Pages : 142
Get Book Here
Book Description
