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Performance Characteristics At Mach Numbers Up To 1 29 Of A Blow In Door Ejector Nozzle With Doors Fixed In Full Open Position 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 Performance Characteristics At Mach Numbers Up To 1 29 Of A Blow In Door Ejector Nozzle With Doors Fixed In Full Open Position book. This book definitely worth reading, it is an incredibly well-written.
Author : Anonim
Publisher : Unknown
Page : 188 pages
File Size : 40,6 Mb
Release : 1967
Category : Electronic
ISBN : NASA:31769000665219
Author : Albert L. Johns,Fred W. Steffen
Publisher : Unknown
Page : 68 pages
File Size : 48,7 Mb
Release : 1970
Category : Electronic
ISBN : STANFORD:36105024774270
Author : Donald P. Hearth
Publisher : Unknown
Page : 52 pages
File Size : 43,9 Mb
Release : 1956
Category : Aerodynamics, Supersonic
ISBN : UOM:39015086463786
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.
Author : Anonim
Publisher : Unknown
Page : 54 pages
File Size : 49,6 Mb
Release : 1961
Category : Electronic
ISBN : NASA:31769000459530
Author : Paige B. Burbank
Publisher : Unknown
Page : 52 pages
File Size : 48,7 Mb
Release : 1951
Category : Mach number
ISBN : UOM:39015086464735
A method of designing an aymmetric, fixed-geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was a constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.02 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Author : Richard J. Re
Publisher : Unknown
Page : 202 pages
File Size : 47,5 Mb
Release : 2001
Category : Mach number
ISBN : NASA:31769000451933
Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.
Author : B. S. Stratford,G. E. Sansome
Publisher : Unknown
Page : 0 pages
File Size : 42,5 Mb
Release : 1962
Category : Supersonic nozzles
ISBN : OCLC:6169394
Author : Francis J. Capone
Publisher : Unknown
Page : 308 pages
File Size : 49,8 Mb
Release : 1980
Category : Electronic
ISBN : NASA:31769000431075
Author : United States. Flight Standards Service
Publisher : Unknown
Page : 620 pages
File Size : 46,7 Mb
Release : 1976
Category : Airframes
ISBN : IND:30000044908899
Author : I. E. Idelchik
Publisher : Unknown
Page : 0 pages
File Size : 46,9 Mb
Release : 2005
Category : Fluid dynamics
ISBN : 8179921182
The handbook has been composed on the basis of processing, systematization and classification of the results of a great number of investigations published at different time. The essential part of the book is the outcome of investigations carried out by the author. The present edition of this handbook should assist in increasing the quality and efficiency of the design and usage of indutrial power engineering and other constructions and also of the devices and apparatus through which liquids and gases move.
Author : Theo W. Knacke
Publisher : Unknown
Page : 524 pages
File Size : 44,9 Mb
Release : 1992
Category : Sports & Recreation
ISBN : PSU:000043624584
The purpose of this manual is to provide recovery system engineers in government and industry with tools to evaluate, analyze, select, and design parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, concept analysis, parachute performance, force and stress analysis, material selection, parachute assembly and component design, and manufacturing. Experienced recovery system engineers will find this publication useful as a technical reference book; recent college graduates will find it useful as a textbook for learning about parachutes and parachute recovery systems; and technicians with extensive practical experience will find it useful as an engineering textbook that includes a chapter on parachute- related aerodynamics. In this manual, emphasis is placed on aiding government employees in evaluating and supervising the design and application of parachute systems. The parachute recovery system uses aerodynamic drag to decelerate people and equipment moving in air from a higher velocity to a lower velocity and to a safe landing. This lower velocity is known as rate of descent, landing velocity, or impact velocity, and is determined by the following requirements: (1) landing personnel uninjured and ready for action, (2) landing equipment and air vehicles undamaged and ready for use or refurbishment, and (3) impacting ordnance at a preselected angle and velocity.
Author : T. A. Heppenheimer
Publisher : Unknown
Page : 364 pages
File Size : 52,9 Mb
Release : 2006
Category : Science
ISBN : PURD:32754079096438
Hypersonics is the study of flight at speeds where aerodynamic heating dominates the physics of the problem. Typically this is Mach 5 and higher. Hypersonics is an engineering science with close links to supersonics and engine design. Within this field, many of the most important results have been experimental. The principal facilities have been wind tunnels and related devices, which have produced flows with speeds up to orbital velocity. Why is it important? Hypersonics has had two major applications. The first has been to provide thermal protection during atmospheric entry. Success in this enterprise has supported ballistic-missile nose cones, has returned strategic reconnaissance photos from orbit and astronauts from the Moon, and has even dropped an instrument package into the atmosphere of Jupiter. The last of these approached Jupiter at four times the speed of a lunar mission returning to Earth. Work with re-entry has advanced rapidly because of its obvious importance. The second application has involved high-speed propulsion and has sought to develop the scramjet as an advanced airbreathing ramjet. Scramjets are built to run cool and thereby to achieve near-orbital speeds. They were important during the Strategic Defense Initiative, when a set of these engines was to power the experimental X-30 as a major new launch vehicle. This effort fell short, but the X-43A, carrying a scramjet, has recently flown at Mach 9.65 by using a rocket. Atmospheric entry today is fully mature as an engineering discipline. Still, the Jupiter experience shows that work with its applications continues to reach for new achievements. Studies of scramjets, by contrast, still seek full success, in which such engines can accelerate a vehicle without the use of rockets. Hence, there is much to do in this area as well. For instance, work with computers may soon show just how good scramjets can become. NASA SP-2007-4232
Author : Jeremy R. Kinney
Publisher : Government Printing Office
Page : 318 pages
File Size : 42,5 Mb
Release : 2018-02-15
Category : Airplanes
ISBN : 1626830371
The NACA and aircraft propulsion, 1915-1958 -- NASA gets to work, 1958-1975 -- The shift toward commercial aviation, 1966-1975 -- The quest for propulsive efficiency, 1976-1989 -- Propulsion control enters the computer era, 1976-1998 -- Transiting to a new century, 1990-2008 -- Toward the future
Author : Jack D. Mattingly
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 0 pages
File Size : 48,5 Mb
Release : 2005
Category : Aircraft gas-turbines
ISBN : 1563477785
This text provides an introduction to gas turbine engines and jet propulsion for aerospace or mechanical engineers. The text is divided into four parts: introduction to aircraft propulsion; basic concepts and one-dimensional/gas dynamics; parametric (design point) and performance (off-design) analysis of air breathing propulsion systems; and analysis and design of major gas turbine engine components (fans, compressors, turbines, inlets, nozzles, main burners, and afterburners). Design concepts are introduced early (aircraft performance in introductory chapter) and integrated throughout. Written with extensive student input on the design of the book, the book builds upon definitions and gradually develops the thermodynamics, gas dynamics, and gas turbine engine principles.
Author : Barnes Warnock McCormick
Publisher : Courier Corporation
Page : 356 pages
File Size : 43,8 Mb
Release : 1999-01-01
Category : Technology & Engineering
ISBN : 0486404609
An extremely practical overview of V/STOL (vertical/short takeoff and landing) aerodynamics, this volume offers a presentation of general theoretical and applied aerodynamic principles, covering propeller and helicopter rotor theory for both the static and forward flight cases. Both a text for students and a reference for professionals, the book can be used for advanced undergraduate or graduate courses. Numerous detailed figures, plus exercises. 1967 edition. Preface. Appendix. Index.