Experimental Evaluation of Supersonic Wind Tunnel Performance with Solid Wall Test Section - Supersonic Diffuser - Scavenging Scoop Combinations 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 Experimental Evaluation of Supersonic Wind Tunnel Performance with Solid Wall Test Section - Supersonic Diffuser - Scavenging Scoop Combinations PDF full book. Access full book title Experimental Evaluation of Supersonic Wind Tunnel Performance with Solid Wall Test Section - Supersonic Diffuser - Scavenging Scoop Combinations by R. V. DeLeo. Download full books in PDF and EPUB format.
Author: R. V. DeLeo Publisher: ISBN: Category : Supersonic wind tunnels Languages : en Pages : 82
Book Description
An experimental evaluation of wind tunnel performance has been conducted for the University of Minnesota by the Rosemount Aeronautical Laboratories within a test section Mach number range of 1.5 to 4.4. In order to evaluate the effect of the addition of various scavenge ducts to the basic wind tunnel configuration, the performance of a solid wall test section - adjustable diffuser combination was determined both with and without a scavenging duct present.
Author: R. V. DeLeo Publisher: ISBN: Category : Supersonic wind tunnels Languages : en Pages : 82
Book Description
An experimental evaluation of wind tunnel performance has been conducted for the University of Minnesota by the Rosemount Aeronautical Laboratories within a test section Mach number range of 1.5 to 4.4. In order to evaluate the effect of the addition of various scavenge ducts to the basic wind tunnel configuration, the performance of a solid wall test section - adjustable diffuser combination was determined both with and without a scavenging duct present.
Author: Rudolf Hermann Publisher: ISBN: Category : Wind tunnels Languages : en Pages : 90
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: R. V. DeLeo
Author: R. V. DeLeo
Author: R. V. De Leo
Author: George Rudinger
Author: Johns Hopkins University. Applied Physics Laboratory
Author: 
Author: Rudolf Hermann
Author: Harris M. Schurmeier
Author: 
Author: Defense Documentation Center (U.S.)
Author: