Download or read book Dynamic Response of a Mach 2 5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction written by Joseph F. Wasserbauer and published by . This book was released on 1969 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Dynamic response of supersonic mixed compression inlet coupled to cold pipe or turbojet engine.

Download or read book NASA Technical Note written by and published by . This book was released on 1969 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Memorandum written by and published by . This book was released on 1969 with total page 882 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Dynamic Distortion in a Mach 2 50 Inlet with 60 Percent Internal Contraction and Its Effect on Turbojet Stall Margin written by James E. Calogeras and published by . This book was released on 1969 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1971 with total page 1180 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Literature Search of Publications Concerning the Prediction of Dynamic Inlet Flow Distortion and Related Topics written by William G. Schweikhard and published by . This book was released on 1983 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt: Publications prior to March 1981 were surveyed to determine inlet flow dynamic distortion prediction methods and to catalog experimental and analytical information concerning inlet flow dynamic distortion prediction methods and to catalog experimental and analytical information concerning inlet flow dynamics at the engine-inlet interface of conventional aircraft (excluding V/STOL). The sixty-five publications found are briefly summarized and tabulated according to topic and are cross-referenced according to content and nature of the investigation (e.g., predictive, experimental, analytical and types of tests). Three appendices include lists of references, authors, organizations and agencies conducting the studies. Also, selected materials summaries, introductions and conclusions - from the reports are included. Few reports were found covering methods for predicting the probable maximum distortion. The three predictive methods found are those of Melick, Jacox and Motycka. The latter two require extensive high response pressure measurements at the compressor face, while the Melick Technique can function with as few as one or two measurements.

Download or read book Experimental Investigation of Dynamic Distortion in a Mach 2 50 Inlet with 60 Percent Internal Contraction and Its Effect on Turbojet Stall Margin written by and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Dynamic Response of a Mach 2 5 Axisymmetric Inlet with Engine Or Cold Pipe and Utilizing 60 Percent Supersonic Internal Area Contraction written by Joseph F. Wasserbauer and published by . This book was released on 1969 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Dynamic Response of a Two dimensional Mach 2 7 Mixed compression Inlet written by Robert J. Baumbick and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted on a two-dimensional supersonic inlet. Internal disturbances in diffuser exit mass flow were produced by oscillating overboard bypass doors. Open-loop dynamic responses of shock position, throat exit and diffuser exit static pressures are presented. The steady-state and dynamic coupling between ducts were also obtained. The experimental results from the two-dimensional inlet are compared to results from a similar size axisymmetric inlet and also to a transfer function synthesis program.

Download or read book Terminal shock and Restart Control of a Mach 2 5 Axisymmetric Mixed Compression Inlet with 40 Percent Internal Contraction written by Robert J. Baumbick and published by . This book was released on 1974 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of experimental tests conducted on a supersonic, mixed-compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was coupled to either a choked orifice plate or a long duct which had a variable-area choked exit plug. Closed-loop frequency responses of selected diffuser static pressures used in the terminal-shock control system are presented. Results are shown for Mach 2.5 conditions with the inlet coupled to either the choked orifice plate or the long duct. Inlet unstart-restart traces are also presented. High-response inlet bypass doors were used to generate an internal disturbance and also to achieve terminal-shock control.

Download or read book Dynamic Response of Mach 2 5 Axisymmetric Inlet with 40 Percent Supersonic Internal Area Contraction written by Robert J. Baumbick and published by . This book was released on 1973 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Instantaneous Distortion in a Mach 2 5 40 percent internal contraction Inlet and Its Effect on Turbojet Stall Margin written by Paul L. Burstadt and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeroacoustics of Flight Vehicles written by Harvey H. Hubbard and published by . This book was released on 1991 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aircraft Propulsion written by Saeed Farokhi and published by John Wiley & Sons. This book was released on 2014-04-01 with total page 1052 pages. Available in PDF, EPUB and Kindle. Book excerpt: New edition of the successful textbook updated to include new material on UAVs, design guidelines in aircraft engine component systems and additional end of chapter problems Aircraft Propulsion, Second Edition follows the successful first edition textbook with comprehensive treatment of the subjects in airbreathing propulsion, from the basic principles to more advanced treatments in engine components and system integration. This new edition has been extensively updated to include a number of new and important topics. A chapter is now included on General Aviation and Uninhabited Aerial Vehicle (UAV) Propulsion Systems that includes a discussion on electric and hybrid propulsion. Propeller theory is added to the presentation of turboprop engines. A new section in cycle analysis treats Ultra-High Bypass (UHB) and Geared Turbofan engines. New material on drop-in biofuels and design for sustainability is added to refl ect the FAA’s 2025 Vision. In addition, the design guidelines in aircraft engine components are expanded to make the book user friendly for engine designers. Extensive review material and derivations are included to help the reader navigate through the subject with ease. Key features: General Aviation and UAV Propulsion Systems are presented in a new chapter Discusses Ultra-High Bypass and Geared Turbofan engines Presents alternative drop-in jet fuels Expands on engine components' design guidelines The end-of-chapter problem sets have been increased by nearly 50% and solutions are available on a companion website Presents a new section on engine performance testing and instrumentation Includes a new 10-Minute Quiz appendix (with 45 quizzes) that can be used as a continuous assessment and improvement tool in teaching/learning propulsion principles and concepts Includes a new appendix on Rules of Thumb and Trends in aircraft propulsion Aircraft Propulsion, Second Edition is a must-have textbook for graduate and undergraduate students, and is also an excellent source of information for researchers and practitioners in the aerospace and power industry.

Download or read book Gas Turbine Engineering Handbook written by Meherwan P. Boyce and published by Elsevier. This book was released on 2017-09-01 with total page 956 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Gas Turbine Engineering Handbook has been the standard for engineers involved in the design, selection, and operation of gas turbines. This revision includes new case histories, the latest techniques, and new designs to comply with recently passed legislation. By keeping the book up to date with new, emerging topics, Boyce ensures that this book will remain the standard and most widely used book in this field. The new Third Edition of the Gas Turbine Engineering Hand Book updates the book to cover the new generation of Advanced gas Turbines. It examines the benefit and some of the major problems that have been encountered by these new turbines. The book keeps abreast of the environmental changes and the industries answer to these new regulations. A new chapter on case histories has been added to enable the engineer in the field to keep abreast of problems that are being encountered and the solutions that have resulted in solving them. Comprehensive treatment of Gas Turbines from Design to Operation and Maintenance. In depth treatment of Compressors with emphasis on surge, rotating stall, and choke; Combustors with emphasis on Dry Low NOx Combustors; and Turbines with emphasis on Metallurgy and new cooling schemes. An excellent introductory book for the student and field engineers A special maintenance section dealing with the advanced gas turbines, and special diagnostic charts have been provided that will enable the reader to troubleshoot problems he encounters in the field The third edition consists of many Case Histories of Gas Turbine problems. This should enable the field engineer to avoid some of these same generic problems

Download or read book Facing the Heat Barrier written by T. A. Heppenheimer and published by Government Printing Office. This book was released on 2009-08 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonics is the study of flight at speeds where aerodynamic heating dominates the physics of the problem. It 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 this important? Hypersonics has had two major applications. The first has been to provide thermal protection during atmospheric reentry. 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 second application has involved high-speed propulsion and has sought to develop the scramjet as an advanced airbreathing ramjet. Atmospheric entry today is fully mature as an engineering discipline, but work with its applications continues to reach for new achievements. Studies of scramjets 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.

Download or read book Experimental Investigation of a Large scale Two dimensional Mixed compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.