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An Investigation of Screens for Removing Distortions in Ducted Flows at High Subsonic Speeds

Charles C. Wood
An Investigation of Screens for Removing Distortions in Ducted Flows at High Subsonic Speeds by Charles C. Wood PDF

Author : Charles C. Wood
Publisher :
Page : 63 pages
File Size : 15,27 MB
Release : 1957
Category : Air ducts
ISBN :

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In order to aid in the research concerning the problem of obtaining uniform flow in ducts, an investigation of resistance was conducted for the purposes of (1) providing systematic data for the Mach number range from 0.20 to 0.65 on the flow smoothing effect of screens for various types of flow nonuniformities together with the consequent cost of total-pressure losses required to accomplish various degrees of flow smoothing, and (3) summarizing the data in the literature on screen total-pressure losses in a convenient form suitable for engineering studies. The experimental data were obtained in a directly connected rectangular duct in which the nonuniform flow distributions were produced by spoilers located upstream from the screens.

NASA Memorandum

NASA Memorandum by PDF

Author :
Publisher :
Page : 44 pages
File Size : 30,63 MB
Release : 1958
Category : Aeronautics
ISBN :

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Distortion Induced Engine Instability

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Distortion Induced Engine Instability by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development PDF

Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher :
Page : 194 pages
File Size : 32,55 MB
Release : 1974
Category : Aerodynamics
ISBN :

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NASA Memorandum

United States. National Aeronautics and Space Administration
NASA Memorandum by United States. National Aeronautics and Space Administration PDF

Author : United States. National Aeronautics and Space Administration
Publisher :
Page : 438 pages
File Size : 24,59 MB
Release : 1959
Category : Aeronautics
ISBN :

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Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles

Donald P. Hearth
Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles by Donald P. Hearth PDF

Author : Donald P. Hearth
Publisher :
Page : 52 pages
File Size : 36,52 MB
Release : 1956
Category : Aerodynamics, Supersonic
ISBN :

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The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height relative to the boundary-layer thickness. The pressure recovery increased at about the same rate as theoretically predicted for an inlet in a boundary layer having a one-seventh power profile, but was only about 0.68 to 0.75 of the theoretically obtainable values. Under some operating conditions, flow from the primary jet was exhausted through the auxiliary inlet. This phenomenon could be predicted from the ejector pumping characteristics.

AGARD Lecture Series

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
AGARD Lecture Series by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development PDF

Author : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher :
Page : 596 pages
File Size : 32,92 MB
Release : 199?
Category : Aeronautics
ISBN :

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