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An Experimental Investigation Of A Supersonic Two Dimensional Perforated Inlet At A Nominal Free Stream Mach Number Of 25
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Author :University of Toronto. Institute of Aerophysics Publisher :University of Toronto, Institute of Aerophysics ISBN 13 : Total Pages :15 pages Book Rating :4.:/5 (249 download)
Book Synopsis An Experimental Investigation of a Supersonic Two-dimensional Perforated Inlet at a Nominal Free Stream Mach Number of 2.5 by : University of Toronto. Institute of Aerophysics
Download or read book An Experimental Investigation of a Supersonic Two-dimensional Perforated Inlet at a Nominal Free Stream Mach Number of 2.5 written by University of Toronto. Institute of Aerophysics and published by University of Toronto, Institute of Aerophysics. This book was released on 1958 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System by : Norman D. Wong
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.
Book Synopsis Supersonic Inlets by : Ione D. V. Faro
Download or read book Supersonic Inlets written by Ione D. V. Faro and published by . This book was released on 1965 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design and operation of supersonic inlets is discussed. The means by which the incoming flow may be decelerated to a subsonic velocity are enumerated and evaluated. This report covers diffusers which employ internal compression, external compression or a combination of the two. Experimentally determined values of the total pressure recovery, the capture-area ratio and the inlet drag are compared with those determined from available theories for all types of diffusers. The discussions which in general refer to axisymmetric configurations usually may be applied with equal validity to two-dimensional diffusers. However, some specific problems of the latter are treated. The effects of boundary layer are considered in some detail as are the problems of oscillating flow. (Author).
Book Synopsis Pathway to Excellence by : Gordon N. Patterson
Download or read book Pathway to Excellence written by Gordon N. Patterson and published by . This book was released on 1977 with total page 316 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1960 with total page 1006 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Axially Symmetric and Two-dimensional Multinozzles for Producing Supersonic Streams by : Eli Reshotko
Download or read book Investigation of Axially Symmetric and Two-dimensional Multinozzles for Producing Supersonic Streams written by Eli Reshotko and published by . This book was released on 1952 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Canadiana written by and published by . This book was released on 1969 with total page 1054 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Progress Report on Research Supported by Grants from the Defense Research Board of Canada by : University of Toronto. Institute for Aerospace Studies
Download or read book Progress Report on Research Supported by Grants from the Defense Research Board of Canada written by University of Toronto. Institute for Aerospace Studies and published by . This book was released on 1990 with total page 378 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Two-dimensional, Supersonic Cascade-type Inlets at a Mach Number of 3.11 by : Edward Offenhartz
Download or read book An Experimental Investigation of Two-dimensional, Supersonic Cascade-type Inlets at a Mach Number of 3.11 written by Edward Offenhartz and published by . This book was released on 1954 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Progress Report by : University of Toronto. Institute for Aerospace Studies
Download or read book Annual Progress Report written by University of Toronto. Institute for Aerospace Studies and published by . This book was released on 1954 with total page 1014 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Bulletin and Annual Progress Report by :
Download or read book Bulletin and Annual Progress Report written by and published by . This book was released on 1959 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Investigation of a Variable Mach Number Two-dimensional Supersonic Tunnel of Fixed Geometry by : William J. Nelson
Download or read book Preliminary Investigation of a Variable Mach Number Two-dimensional Supersonic Tunnel of Fixed Geometry written by William J. Nelson and published by . This book was released on 1949 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed by : Leonard E. Stitt
Download or read book Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed written by Leonard E. Stitt and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal by : Earl C. Watson
Download or read book An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal written by Earl C. Watson and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 by : Frederick K. Hube
Download or read book Wind Tunnel Tests of Supersonic Two-dimensional and Half-axisymmetric Inlet Models in a Nonuniform Flow Field at Mach Numbers from 1.5 Through 2.5 written by Frederick K. Hube and published by . This book was released on 1971 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722219505 Total Pages :46 pages Book Rating :4.2/5 (195 download)
Book Synopsis Experimental Investigation of the Performance of a Mach-2. 7 Two-Dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental Investigation of the Performance of a Mach-2. 7 Two-Dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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. Wasserbauer, J. F. and Meleason, E. T. and Burstadt, P. L. Glenn Research Center RTOP 537-02-23...
Book Synopsis Experimental Investigation of a Large Scale, Two-dimensional, Mixed-compression Inlet System by : Warren E. Anderson
Download or read book Experimental Investigation of a Large Scale, Two-dimensional, Mixed-compression Inlet System written by Warren E. Anderson and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
