Author: R. V. De LeoPublisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
Experimental Evaluation of Transonic Wind Tunnel Performance with Solid Wall Test Section-diffuser-scavenging Scoop Combinations
Author: R. V. De LeoExperimental Evaluation of Supersonic Wind Tunnel Performance with Solid Wall Test Section - Supersonic Diffuser - Scavenging Scoop Combinations
Author: R. V. DeLeoPublisher:
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.
U.S. Government Research Reports
Author: Subject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)Publisher:
ISBN:
Category : Science
Languages : en
Pages : 296
Book Description
Proceedings of the Conference
Author: Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 620
Book Description
Wind Tunnel Test Techniques
Author: Colin BritcherPublisher: Academic Press
ISBN: 0128181001
Category : Technology & Engineering
Languages : en
Pages : 672
Book Description
Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed Provides a discussion of similarity laws as well as material on statistical analysis Includes coverage on facility-to-facility and facility-to-CFD correlation Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing
Bibliography of Scientific and Industrial Reports
Author: Experiments to Assess the Influence of Changes in the Tunnel Wall Boundary Layer on Transonic Wall Crossflow Characteristics
Author: R. F. StarrPublisher:
ISBN:
Category : Transonic wind tunnels
Languages : en
Pages : 32
Book Description
The equivalent porosity of the test section wall in a transonic wind tunnel with a fixed geometric porosity and varying wall boundary-layer displacement thickness, has been investigated. Previous experiments have demonstrated that the boundary-layer displacement thickness on the wall influences the wall crossflow characteristic. Experimental data from a Ludwieg tube type of transonic tunnel are compared with data from conventional transonic tunnels in the Mach number range from 0.95 to 1.15. The displacement thickness studied is comparatively thin and represents typical values which will be encountered in future high Reynolds number transonic tunnels.
Aeronautical Engineering Review
Author: Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section
Author: Rudolf HermannPublisher:
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.