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Quiescent Air Performance Of A Truncated Turbojet Plug Nozzle With Shroud And Plug Base Flows From A Common Source Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Quiescent Air Performance Of A Truncated Turbojet Plug Nozzle With Shroud And Plug Base Flows From A Common Source book. This book definitely worth reading, it is an incredibly well-written.
Author : Albert L. Johns
Publisher : Unknown
Page : 38 pages
File Size : 47,8 Mb
Release : 1969
Category : Electronic
ISBN : STANFORD:36105024772696
Author : Albert L. Johns
Publisher : Unknown
Page : 40 pages
File Size : 50,5 Mb
Release : 1969
Category : Electronic
ISBN : NASA:31769001175903
Author : Anonim
Publisher : Unknown
Page : 882 pages
File Size : 49,9 Mb
Release : 1976
Category : Aeronautics
ISBN : UOM:39015040296553
Author : Anonim
Publisher : Unknown
Page : 116 pages
File Size : 44,7 Mb
Release : 1977
Category : Astronautics
ISBN : OSU:32435020935268
Author : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher : Unknown
Page : 966 pages
File Size : 40,7 Mb
Release : 1970
Category : Aeronautics
ISBN : STANFORD:36105113793769
Author : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher : Unknown
Page : 962 pages
File Size : 52,9 Mb
Release : 1970
Category : Aeronautics
ISBN : CORNELL:31924057848867
Author : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher : Unknown
Page : 956 pages
File Size : 49,7 Mb
Release : 1970
Category : Science
ISBN : NASA:31769000659238
Author : Anonim
Publisher : Unknown
Page : 384 pages
File Size : 48,6 Mb
Release : 1969
Category : Aeronautics
ISBN : UIUC:30112106767210
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 : Anonim
Publisher : Unknown
Page : 784 pages
File Size : 50,9 Mb
Release : 1969-10
Category : Science
ISBN : NYPL:33433066455688
Author : Douglas E. Harrington,Stanley M. Nosek,David M. Straight
Publisher : Unknown
Page : 44 pages
File Size : 41,6 Mb
Release : 1974
Category : Jet nozzles
ISBN : UIUC:30112106661660
Author : Douglas E. Harrington,James J. Schloemer,Stanley A. Skebe
Publisher : Unknown
Page : 44 pages
File Size : 43,7 Mb
Release : 1976
Category : Airplanes
ISBN : UIUC:30112106612978
Author : Douglas E. Harrington,James J. Schloemar
Publisher : Unknown
Page : 44 pages
File Size : 54,8 Mb
Release : 1974
Category : Airplanes
ISBN : STANFORD:36105024782695
Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.
Author : Douglas E. Harrington
Publisher : Unknown
Page : 60 pages
File Size : 44,6 Mb
Release : 1970
Category : Electronic
ISBN : NASA:31769001178170
Author : Douglas E. Harrington
Publisher : Unknown
Page : 52 pages
File Size : 47,6 Mb
Release : 1975
Category : Airplanes
ISBN : UIUC:30112105150129
Author : Stanley M. Nosek,David M. Straight
Publisher : Unknown
Page : 29 pages
File Size : 42,5 Mb
Release : 1976
Category : Airplanes
ISBN : STANFORD:36105024824364
Plug nozzle film cooling data were obtained downstream of a slot located at 42 percent of the total plug length on a J-85 engine. Film cooling reduced the aft end wall temperature as much as 150 K, reduced total pressure loss in the upstream convection cooling passages by 50 percent, and reduced estimated compressor bleed flow requirement by 14 percent compared to an all convectively cooled nozzle. Shock waves along the plug surface strongly influenced temperature distributions on both convection and film cooled portions. The effect was most severe at nozzle pressure ratios below 10 where adverse pressure gradients were most severe.
