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Author : Warren E. Anderson,Norman D. Wong
Publisher : Unknown
Page : 68 pages
File Size : 43,7 Mb
Release : 1970
Category : Jet engines
ISBN : STANFORD:36105024774346
Author : Norman D. Wong
Publisher : Unknown
Page : 68 pages
File Size : 48,8 Mb
Release : 1971
Category : Jet engines
ISBN : UIUC:30112106747188
A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Author : Norman D. Wong,Warren E. Anderson
Publisher : Unknown
Page : 52 pages
File Size : 40,7 Mb
Release : 1973
Category : Drag (Aerodynamics)
ISBN : UIUC:30112106600064
A large scale, variable-geometry inlet system with a design Mach number of 3.0 was tested at Mach numbers from 0.6 to 1.28. Variable features for off-design operation are an adjustable-height ramp system and a translating cowl.
Author : Warren E. Anderson,Norman D. Wong
Publisher : Unknown
Page : 68 pages
File Size : 54,5 Mb
Release : 1970
Category : Jet engines
ISBN : NASA:31769001177537
Author : Anonim
Publisher : Unknown
Page : 104 pages
File Size : 48,8 Mb
Release : 1980
Category : Aeronautics
ISBN : MINN:31951000845247A
Author : Anonim
Publisher : Unknown
Page : 520 pages
File Size : 41,5 Mb
Release : 1974
Category : Electronic
ISBN : MINN:31951000846499E
Author : Anonim
Publisher : Unknown
Page : 1570 pages
File Size : 47,6 Mb
Release : 1974
Category : Government publications
ISBN : STANFORD:36105006329010
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1408 pages
File Size : 44,5 Mb
Release : 1976
Category : United States
ISBN : STANFORD:36105021034173
Author : Anonim
Publisher : Unknown
Page : 464 pages
File Size : 53,7 Mb
Release : 1995
Category : Aeronautics
ISBN : MINN:30000011064593
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 : 276 pages
File Size : 48,7 Mb
Release : 1974
Category : Mechanics, Applied
ISBN : UCAL:C2682448
Author : Donald B. Smeltzer,Norman E. Sorensen
Publisher : Unknown
Page : 252 pages
File Size : 46,7 Mb
Release : 1970
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106880799
Author : Yuri Bazilevs,Kenji Takizawa
Publisher : Birkhäuser
Page : 500 pages
File Size : 46,6 Mb
Release : 2016-10-04
Category : Mathematics
ISBN : 9783319408279
This contributed volume celebrates the work of Tayfun E. Tezduyar on the occasion of his 60th birthday. The articles it contains were born out of the Advances in Computational Fluid-Structure Interaction and Flow Simulation (AFSI 2014) conference, also dedicated to Prof. Tezduyar and held at Waseda University in Tokyo, Japan on March 19-21, 2014. The contributing authors represent a group of international experts in the field who discuss recent trends and new directions in computational fluid dynamics (CFD) and fluid-structure interaction (FSI). Organized into seven distinct parts arranged by thematic topics, the papers included cover basic methods and applications of CFD, flows with moving boundaries and interfaces, phase-field modeling, computer science and high-performance computing (HPC) aspects of flow simulation, mathematical methods, biomedical applications, and FSI. Researchers, practitioners, and advanced graduate students working on CFD, FSI, and related topics will find this collection to be a definitive and valuable resource.
Author : Joseph F. Wasserbauer
Publisher : Unknown
Page : 50 pages
File Size : 49,7 Mb
Release : 1996
Category : Electronic
ISBN : NASA:31769000608524
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position.
Author : Anonim
Publisher : Unknown
Page : 442 pages
File Size : 49,9 Mb
Release : 1989
Category : Airplanes
ISBN : PSU:000017116763
Author : Mark R. Nichols
Publisher : Unknown
Page : 100 pages
File Size : 51,8 Mb
Release : 1980
Category : Aerodynamics
ISBN : UIUC:30112105146044
