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Investigation Of The Supersonic Through Flow Compressor Concept Volume I Performance Potential And Mechanical Design Study Of The Supersonic Inflow Engine
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Book Synopsis Investigation of the Supersonic Through-flow Compressor Concept. Volume I. Performance Potential and Mechanical Design Study of the Supersonic Inflow Engine by : Robert L. O'Brien
Download or read book Investigation of the Supersonic Through-flow Compressor Concept. Volume I. Performance Potential and Mechanical Design Study of the Supersonic Inflow Engine written by Robert L. O'Brien and published by . This book was released on 1967 with total page 97 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to evaluate the performance potential of the supersonic inflow turbojet engine (SSIFE) utilizing a supersonic through-flow compressor. The engines considered in this study were designed to operate as accelerators at flight Mach numbers up to 3.5 in the 1980 time period. During the preliminary phases of this study, both cruise and the accelerator engines were considered. The program consisted of a preliminary study of compressor and engine configurations, followed by detailed compressor and engine performance investigations. Experimental investigations of supersonic cascade and diffuser performance were also conducted to provide experimental information required to evaluate this concept. Concurrent with this funded program a corporate-sponsored program was also conducted to evaluate the performance potential of supersonic combustion in the SSIFE and to generate a practical mechanical design for this engine. This report is intended to serve as a summary of all of the work performed on the supersonic inflow engine concept. Comparisons were made between the performance and mechanical design of both the SSIFE and an advanced turbojet sized to produce the same transonic thrust. The SSIFE evolved during the design study was 42 percent shorter, had the same frontal area, and approximately 15 percent greater installed weight than the advanced turbojet. The results obtained from component tests of supersonic cascades and the downstream supersonic diffuser were in general agreement with the level of compression system performance estimated for the engine analyses. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 628 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Axial Velocity Compressor Study. Volume i - Summary and Aerodynamic Design Studies by : F. W. Lipfert
Download or read book Supersonic Axial Velocity Compressor Study. Volume i - Summary and Aerodynamic Design Studies written by F. W. Lipfert and published by . This book was released on 1967 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume presents the aerodynamic design studies conducted in the investigation of a supersonic axial velocity compressor turbojet. Feasibility was shown, and a high temperature turbojet (ASCOT) engine was designed around a compressor featuring direct entry of supersonic flow during supersonic flight. The aerodynamic requirements of each of the components were specified, and engine performance data were computed for hydrogen and hydrocarbon fuels. (Author).
Book Synopsis Performance of Supersonic Axial-flow Compressors Based on One-dimensional Analysis by : Linwood C. Wright
Download or read book Performance of Supersonic Axial-flow Compressors Based on One-dimensional Analysis written by Linwood C. Wright and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Investigation of Subsonic and Supersonic Flow in a Radial Inflow Compressor by : Yadiyurappa Siddaveerasetty Bale
Download or read book Investigation of Subsonic and Supersonic Flow in a Radial Inflow Compressor written by Yadiyurappa Siddaveerasetty Bale and published by . This book was released on 1970 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of an Axial-flow Supersonic Compressor Having Sharp Leading-edge Blades with an 8-percent Mean Thickness-chord Ratio by : Theodore J. Goldberg
Download or read book Experimental Investigation of an Axial-flow Supersonic Compressor Having Sharp Leading-edge Blades with an 8-percent Mean Thickness-chord Ratio written by Theodore J. Goldberg and published by . This book was released on 1955 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Supersonic Through-flow Compressor Concept. Volume Ii. Analytical and Experimental Investigations of Supersonic Cascades and Diffusers by : Stuart E. Gadbois
Download or read book Investigation of the Supersonic Through-flow Compressor Concept. Volume Ii. Analytical and Experimental Investigations of Supersonic Cascades and Diffusers written by Stuart E. Gadbois and published by . This book was released on 1967 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical and experimental investigation of supersonic cascades and supersonic diffusers having entrance conditions representative of the flow discharging from a supersonic through-flow compressor was conducted. The performance of these cascades was predicted over a range of operating conditions using a one-dimensional analysis which included shock and friction losses. Cascade configurations designed to provide up to 65 deg of total turning were tested at supersonic approach Mach numbers over a range of incidence angles. The experimental results were in general agreement with the theoretical performance predicted by the one-dimensional analysis. The test results indicate that rotor efficiencies on the order of 80 percent can be obtained with a supersonic through-flow compressor. A theoretical analysis of the supersonic diffuser was conducted to evaluate the effects of diffuser geometry, bleed flow ratio, and entrance Mach number on the diffuser pressure recovery. Tests of an annular diffuser model ingesting supersonic flows with various amounts of wakes, swirl and boundary layer were conducted. The experimental results showed these flows can be diffused with a process efficiency greater than 90 percent. (Author).
Book Synopsis Bibliography of Lewis Research Center Technical Publications Announced in 1977 by : Lewis Research Center
Download or read book Bibliography of Lewis Research Center Technical Publications Announced in 1977 written by Lewis Research Center and published by . This book was released on 1978 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt: This compilation of abstracts describes and indexes over 780 technical reports resulting from the scientific and engineering work performed and managed by the Lewis Research Center in 1977. All the publications were announced in the 1977 issues of STAR (Scientific and Technical Aerospace Reports) and/or IAA (International Aerospace Abstracts). Documents cited include research reports, journal articles, conference presentations, patents and patent applications, and theses.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Theoretical Investigation of Some Design Variables for the Supersonic, Axialflow Compressor by : Hugh B. Thompson
Download or read book A Theoretical Investigation of Some Design Variables for the Supersonic, Axialflow Compressor written by Hugh B. Thompson and published by . This book was released on 1948 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722219574 Total Pages :32 pages Book Rating :4.2/5 (195 download)
Book Synopsis Experimental Investigation of the Performance of a Supersonic Compressor Cascade by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental Investigation of the Performance of a Supersonic Compressor Cascade written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from an experimental investigation of a linear, supersonic, compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic of Germany. The cascade design was derived from the near-tip section of a high-through-flow axial flow compressor rotor with a design relative inlet Mach number of 1.61. Test data were obtained over a range of inlet Mach numbers from 1.23 to 1.71, and a range of static pressure ratios and axial-velocity-density ratios (AVDR) at the design inlet condition. Flow velocity measurements showing the wave pattern in the cascade entrance region were obtained using a laser transit anemometer. From these measurements, some unique-incidence conditions were determined, thus relating the supersonic inlet Mach number to the inlet flow direction. The influence of static pressure ratio and AVDR on the blade passage flow and the blade-element performance is described, and an empirical correlation is used to show the influence of these two (independent) parameters on the exit flow angle and total-pressure loss for the design inlet condition. Tweedt, D. L. and Schreiber, H. A. and Starken, H. Glenn Research Center RTOP 505-62-61...
Book Synopsis Performance of Axial-Flow Supersonic Compressor of Xj55-Ff-1 Turbojet Engine by : Nasa Technical Reports Server (Ntrs)
Download or read book Performance of Axial-Flow Supersonic Compressor of Xj55-Ff-1 Turbojet Engine written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-06 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The inlet wide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached. The total-pressure loss through the guide vanes was approximately 1 percent for the unchoked conditions and from 5 to 6 percent when choked.
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Author :North Atlantic Treaty Organization. Research and Technology Organization Publisher : ISBN 13 : Total Pages :342 pages Book Rating :4.E/5 ( download)
Book Synopsis Fluid Dynamics Research on Supersonic Aircraft by : North Atlantic Treaty Organization. Research and Technology Organization
Download or read book Fluid Dynamics Research on Supersonic Aircraft written by North Atlantic Treaty Organization. Research and Technology Organization and published by . This book was released on 1998 with total page 342 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contains the lecture notes prepared for a Special Course on Fluid Dynamics Research on Supersonic Aircraft organized by the RTO Applied Vehicle Technology Panel (AVT). The Course was held at the von Kármán Institute for Fluid Dynamics (VKI) Institute, Rhode-Saint-Genèse, Belgium 25-29 May 1998. The following topics were covered: History & Economics of Supersonic Transports, Supersonic Aerodynamics, Sonic Boom Theory and Minimization, Multi-Point Design Challenges, Vortex Plume Interactions, Propulsion System Design. Presentations on the major world wide supersonic transport programs were also included. The material assembled in this publication was prepared under the combined sponsorship of the RTO Applied Vehicle Technology Panel, the Consultant and Exchange Program of RTO, and the von Kármán Institute (VKI) for Fluid Dynamics.
Book Synopsis Preliminary Investigation of Supersonic Diffusers by : Arthur Kantrowitz
Download or read book Preliminary Investigation of Supersonic Diffusers written by Arthur Kantrowitz and published by . This book was released on 1945 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The deceleration of air from supersonic velocities in channels has been studied. It has become apparent that a normal shock in the diverging part of the diffuser is probably necessary for stable flow, and ways of minimizing the intensity of this shock have been developed. The effect of various geometrical parameters, especially contraction ratio in the entrance region, on the performance of supersonic diffusers has been investigated. By the use of these results, diffusers were designed which, starting without initial boundary layer, recovered 90 percent of the kinetic energy in supersonic air streams up to a Mach number of 1.85.
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
