Experiments to Assess the Influence of Changes in the Tunnel Wall Boundary Layer on Transonic Wall Crossflow Characteristics PDF Download
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Author: R. F. Starr Publisher: 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.
Author: R. F. Starr Publisher: 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.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
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.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
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.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 724
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Publisher: ISBN: Category : Research Languages : en Pages : 1056
Book Description
Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Author: B. F. R. Ewald Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 578
Book Description
This report was compiled by an international team of wind tunnel wall correction experts. It presents the present state of the art in wind tunnel wall corrections with a special emphasis given to the description of modern wall correction methods based on Computational Fluid Dynamics. This AGARDograph was planned by the AGARD Fluid Dynamics Panel to be a modern sequel of the successful AGARDograph 109 "Subsonic Wind Tunnel Wall Corrections", which was published in 1966. AGARDogaph 109 is still valid and continues to be used to provide wall corrections in many wind tunnels. Nevertheless, in the thirty two years since the publication of AGARDograph 109, much work has been done on the subject, and the influence of the new tool of numerical fluid dynamics was so strong, that a sequel to AGARDograph 109 was considered to be necessary.
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher: ISBN: Category : Aeronautics Languages : en Pages : 416
Author: R. F. Starr
Author: R. F. Starr
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Author: T. D. Reed
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Author: B. F. R. Ewald
Author: United States. National Aeronautics and Space Administration
Author: Fan-Ming Yu
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development