Author : Anonim
Publisher : Unknown
Page : 298 pages
File Size : 44,8 Mb
Release : 1976
Category : Aeronautics
ISBN : MINN:31951000844908X
NASA Technical Memorandum
Anonim
Mach 2 5 Performance Of A Bicone Inlet With Internal Focused Compression And 40 Percent Internal Contraction
Mach 2 5 Performance Of A Bicone Inlet With Internal Focused Compression And 40 Percent Internal Contraction 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 Mach 2 5 Performance Of A Bicone Inlet With Internal Focused Compression And 40 Percent Internal Contraction book. This book definitely worth reading, it is an incredibly well-written.
Mach 2.5 Performance of a Bicone Inlet with Internal Focused Compression and 40 Percent Internal Contraction
David A. Choby
Author : David A. Choby
Publisher : Unknown
Page : 68 pages
File Size : 45,5 Mb
Release : 1971
Category : Aerodynamics
ISBN : NASA:31769001179913
Mach 2.5 Performance of a Bicone Inlet with Internal Focused Compression and 40 Percent Internal Contraction by David A. Choby Pdf
Transonic Off-design Drag and Performance of an Axisymmetric Inlet with 40 Percent Internal Contraction on Design
Richard R. Woollett,Edward T. Meleason,David A. Choby
Author : Richard R. Woollett,Edward T. Meleason,David A. Choby
Publisher : Unknown
Page : 64 pages
File Size : 41,6 Mb
Release : 1974
Category : Aerodynamics, Transonic
ISBN : STANFORD:36105024783073
Transonic Off-design Drag and Performance of an Axisymmetric Inlet with 40 Percent Internal Contraction on Design by Richard R. Woollett,Edward T. Meleason,David A. Choby Pdf
An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.
Boundary-layer bleed system study for a full-scale, mixed-compression inlet with 45 percent internal contraction
Robert Joseph Shaw,Joseph F. Wasserbauer,Harvey E. Neumann
Author : Robert Joseph Shaw,Joseph F. Wasserbauer,Harvey E. Neumann
Publisher : Unknown
Page : 72 pages
File Size : 51,8 Mb
Release : 1976
Category : Airplanes
ISBN : UIUC:30112105150707
Boundary-layer bleed system study for a full-scale, mixed-compression inlet with 45 percent internal contraction by Robert Joseph Shaw,Joseph F. Wasserbauer,Harvey E. Neumann Pdf
The results of an experimental bleed development study for a full-scale, Mach 2.5, axisymmetric, mixed-compression inlet were presented. The inlet was designed to satisfy the airflow requirements of the TF30-P-3 turbofan engine. Capabilities for porous bleed on the cowl surface and ram-scoop flush-slot bleed on the centerbody were provided. A configuration with no bleed on the cowl achieved a minimum stable, diffuser exit, total pressure recovery of 0.894 with a centerbody-bleed mass flow ratio of 0.02. Configurations with cowl bleed had minimum stable recoveries as high as 0.900 but suffered range decrement penalties from the increased bleed mass flow removal. Limited inlet stability and unstart angle-of-attack data are presented.
Scientific and Technical Aerospace Reports
Anonim
Author : Anonim
Publisher : Unknown
Page : 128 pages
File Size : 44,6 Mb
Release : 2024-07-02
Category : Aeronautics
ISBN : UOM:39015057252754
Scientific and Technical Aerospace Reports by Anonim Pdf
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.
Distortion in a Full-scale Bicone Inlet with Internal Focused Compression and 45 Percent Internal Contraction
Joseph F. Wasserbauer,Harvey E. Neumann,Robert Joseph Shaw
Author : Joseph F. Wasserbauer,Harvey E. Neumann,Robert Joseph Shaw
Publisher : Unknown
Page : 60 pages
File Size : 43,7 Mb
Release : 1974
Category : Air ducts
ISBN : UIUC:30112106612754
Distortion in a Full-scale Bicone Inlet with Internal Focused Compression and 45 Percent Internal Contraction by Joseph F. Wasserbauer,Harvey E. Neumann,Robert Joseph Shaw Pdf
Experimental Investigation of the Performance of a Mach-2.7 Two-dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction
Joseph F. Wasserbauer
Author : Joseph F. Wasserbauer
Publisher : Unknown
Page : 50 pages
File Size : 50,7 Mb
Release : 1996
Category : Electronic
ISBN : NASA:31769000608524
Experimental Investigation of the Performance of a Mach-2.7 Two-dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction by Joseph F. Wasserbauer Pdf
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.
Functioning of Inorganic/organic Battery Separators in Silver-zinc Cells
Warren H. Philipp
Author : Warren H. Philipp
Publisher : Unknown
Page : 678 pages
File Size : 43,8 Mb
Release : 1976
Category : Electric batteries
ISBN : UFL:31262081360504
Functioning of Inorganic/organic Battery Separators in Silver-zinc Cells by Warren H. Philipp Pdf
Monthly Catalog of United States Government Publications
Anonim
Author : Anonim
Publisher : Unknown
Page : 1014 pages
File Size : 45,6 Mb
Release : 1975
Category : Government publications
ISBN : MINN:31951P01090090Q
Monthly Catalog of United States Government Publications by Anonim Pdf
Data Base for the Prediction of Airframe/propulsion System Interference Effects
Anonim
Author : Anonim
Publisher : Unknown
Page : 444 pages
File Size : 53,7 Mb
Release : 1979
Category : Electronic
ISBN : NASA:31769000736028
Data Base for the Prediction of Airframe/propulsion System Interference Effects by Anonim Pdf
Government Reports Index
Anonim
Author : Anonim
Publisher : Unknown
Page : 954 pages
File Size : 45,9 Mb
Release : 1971
Category : Engineering
ISBN : MSU:31293017237136
Government Reports Index by Anonim Pdf
Aeronautical Engineering
Anonim
Author : Anonim
Publisher : Unknown
Page : 966 pages
File Size : 44,7 Mb
Release : 1971
Category : Aeronautics
ISBN : UIUC:30112075687795
Aeronautical Engineering by Anonim Pdf
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
NASA SP.
Anonim
Author : Anonim
Publisher : Unknown
Page : 632 pages
File Size : 54,6 Mb
Release : 1962
Category : Aeronautics
ISBN : OSU:32435062367040
NASA SP. by Anonim Pdf
Characteristics Study of a Bicone Mixed-compression Inlet for Mach 1.80 to 2.50
Bernhard H. Anderson
Author : Bernhard H. Anderson
Publisher : Unknown
Page : 44 pages
File Size : 41,6 Mb
Release : 1968
Category : Airplanes
ISBN : UIUC:30112106778456
Characteristics Study of a Bicone Mixed-compression Inlet for Mach 1.80 to 2.50 by Bernhard H. Anderson Pdf
Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0
Paul C. Simon,Dennis W. Brown,Ronald G. Huff
Author : Paul C. Simon,Dennis W. Brown,Ronald G. Huff
Publisher : Unknown
Page : 50 pages
File Size : 49,9 Mb
Release : 1957
Category : Aerodynamics, Supersonic
ISBN : UOM:39015086490482