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Effect Of Jet Convergence Angle On The Performance Of Annular Nozzles With Semitoroidal Concave Plugs At Mach Numbers Up To 182
Download Effect Of Jet Convergence Angle On The Performance Of Annular Nozzles With Semitoroidal Concave Plugs At Mach Numbers Up To 182 full books in PDF, epub, and Kindle. Read online Effect Of Jet Convergence Angle On The Performance Of Annular Nozzles With Semitoroidal Concave Plugs At Mach Numbers Up To 182 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effect of Jet Convergence Angle on the Performance of Annular Nozzles with Semitoroidal Concave Plugs at Mach Numbers Up to 1.82 by : Charles E. Mercer
Download or read book Effect of Jet Convergence Angle on the Performance of Annular Nozzles with Semitoroidal Concave Plugs at Mach Numbers Up to 1.82 written by Charles E. Mercer and published by . This book was released on 1972 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an investigation at static conditions and at Mach numbers up to 1.82 are presented for 12 nozzle configurations which have jet convergence angle and jet throat area as geometric parameters. The variation of jet convergence angle from 15 to 40 deg had little effect on the performance of the nozzles having the large value of primary throat area; however, increasing jet convergence angle generally had an adverse effect on performance of the nozzles having the smaller value of primary throat area. The performance of the nozzle configurations with the larger primary throat area is competitive with nozzles designed for operation over the Mach number range.
Book Synopsis Effect of Jet Convergence Angle on the Performance of Annular Nozzles with Semitoroidal Concave Plugs at Mach Numbers Up to 1.82 by : Charles E. Mercer (Aerospace engineer)
Download or read book Effect of Jet Convergence Angle on the Performance of Annular Nozzles with Semitoroidal Concave Plugs at Mach Numbers Up to 1.82 written by Charles E. Mercer (Aerospace engineer) and published by . This book was released on 1972 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an investigation at static conditions and at Mach numbers up to 1.82 are presented for 12 nozzle configurations which have jet convergence angle and jet throat area as geometric parameters. The variation of jet convergence angle from 15 to 40 deg had little effect on the performance of the nozzles having the large value of primary throat area; however, increasing jet convergence angle generally had an adverse effect on performance of the nozzles having the smaller value of primary throat area. The performance of the nozzle configurations with the larger primary throat area is competitive with nozzles designed for operation over the Mach number range.
Book Synopsis Effect of Geometric Parameters on the Static Performance of an Annular Nozzle with a Concave Central Base by : Charles E. Mercer
Download or read book Effect of Geometric Parameters on the Static Performance of an Annular Nozzle with a Concave Central Base written by Charles E. Mercer and published by . This book was released on 1962 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Thrust of an Annular Nozzle with a Concave Central Base by : Blake W. Corson (Jr)
Download or read book Static Thrust of an Annular Nozzle with a Concave Central Base written by Blake W. Corson (Jr) and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.
Book Synopsis Performance of Convergent and Plug Nozzles at Mach Numbers from 0 to 1.97 by : Douglas E. Harrington
Download or read book Performance of Convergent and Plug Nozzles at Mach Numbers from 0 to 1.97 written by Douglas E. Harrington and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of Annular Plug and Expansion-deflection Nozzles Including External Flow Effects at Transonic Mach Numbers by : Robert A. Wasko
Download or read book Performance of Annular Plug and Expansion-deflection Nozzles Including External Flow Effects at Transonic Mach Numbers written by Robert A. Wasko and published by . This book was released on 1968 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Isolated Performance at Mach Numbers From 0.60 to 2.86 of Several Expendable Nozzle Concepts for Supersonic Applications by : Richard J. Re
Download or read book Isolated Performance at Mach Numbers From 0.60 to 2.86 of Several Expendable Nozzle Concepts for Supersonic Applications written by Richard J. Re and published by . This book was released on 2001 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Performance Characteristics of a 10 Deg Conical Plug Nozzle at Mach Numbers Up to 1 29 by :
Download or read book Performance Characteristics of a 10 Deg Conical Plug Nozzle at Mach Numbers Up to 1 29 written by and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Plug and Shroud Geometry Variables on Plug-nozzle Performance at Transonic Speeds by : Bobby L. Berrier
Download or read book Effect of Plug and Shroud Geometry Variables on Plug-nozzle Performance at Transonic Speeds written by Bobby L. Berrier and published by . This book was released on 1969 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Terminal Fairings on the Performance of a Plug-type Exhaust Nozzle in Quiescent Air and at Mach Numbers of 1.62, 1.93, 2.55, and 3.05 by :
Download or read book Effect of Terminal Fairings on the Performance of a Plug-type Exhaust Nozzle in Quiescent Air and at Mach Numbers of 1.62, 1.93, 2.55, and 3.05 written by and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Subsonic Annular Nozzles for Engine Exhaust/external Flow Interaction Studies by : R. J. Matz
Download or read book Investigation of Subsonic Annular Nozzles for Engine Exhaust/external Flow Interaction Studies written by R. J. Matz and published by . This book was released on 1976 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of an experimental investigation to determine the feasibility of conducting engine/external flow interaction tests in subsonic annular airstreams are presented. A representative afterbody model with a 4-in.-diam cylindrical forebody, a faired 15-deg boattail, and a 2.68-in.-diam solid body plume simulator was tested in an 8- by 6-ft porous wall wind tunnel and in annular jets produced by 6-, 8-, and 12-in.-diam nozzles. Afterbody Mach number distributions and boattail pressure drag coefficients obtained on the afterbody in the annular jet were compared with wind tunnel results obtained with boattail approach Mach numbers between 0.5 and 1.0. Boundary-layer profiles were also obtained during the wind tunnel and the annular jet tests.
Book Synopsis Off-design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16.5 by : Bobby L. Berrier
Download or read book Off-design Performance of Two Isentropic Plug Nozzles Designed for a Pressure Ratio of 16.5 written by Bobby L. Berrier and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Angle of Attack and Exit Nozzle Design on the Performance of a 16-inch Ram Jet at Mach Numbers from 1.5 to 2.0 by : Eugene Perchonok
Download or read book Effect of Angle of Attack and Exit Nozzle Design on the Performance of a 16-inch Ram Jet at Mach Numbers from 1.5 to 2.0 written by Eugene Perchonok and published by . This book was released on 1951 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeropulsive Characteristics at Mach Numbers Up to 2.2 of Axisymmetric and Nonaxisymmetric Nozzles Installed on an F-18 Model by : Francis J. Capone
Download or read book Aeropulsive Characteristics at Mach Numbers Up to 2.2 of Axisymmetric and Nonaxisymmetric Nozzles Installed on an F-18 Model written by Francis J. Capone and published by . This book was released on 1982 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation to determine the aeropropulsive characteristics of nonaxisymmetric nozzles on an F-18 jet effects model was conducted in the Langley 16-foot transonic tunnel and the AEDC 16-foot supersonic wind tunnel. The performance of a two dimensional convergent-divergent nozzle, a single expansion ramp nozzle, and a wedge nozzle was compared with that of the baseline axisymmetric nozzle. Test data were obtained at static conditions and at Mach numbers from 0.60 to 2.20 at an angle of attack of 0 deg. Nozzle pressure ratio was varied from jet-off to about 20.
Book Synopsis Effect of Geometric Parameters on the Static Performance of an Annular Nozzle with a Concave Central Base by : Charles E. Mercer
Download or read book Effect of Geometric Parameters on the Static Performance of an Annular Nozzle with a Concave Central Base written by Charles E. Mercer and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of annular convergent nozzles with concave central bases was conducted. The effects of variation in the ratio of annulus-gap width to base radius and the ratio of annulus-gap width to base depth were examined. Thrust performance comparable to that of a conventional convergent nozzle was obtained for those configurations in which the ratio of annulus-gap width to base radius was largest, that is, approximately 0.25. In general, increasing the base depth by extending the turning lip improved thrust performance and increased pressures on the base. (Author).
Book Synopsis Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-jet Afterbody Models with Convergent-divergent Nozzles at Mach Numbers Up to 2.2 by : Odis C. Jr Pendergraft
Download or read book Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-jet Afterbody Models with Convergent-divergent Nozzles at Mach Numbers Up to 2.2 written by Odis C. Jr Pendergraft and published by . This book was released on 1972 with total page 123 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Modern Engineering for Design of Liquid-Propellant Rocket Engines by : Dieter K. Huzel
Download or read book Modern Engineering for Design of Liquid-Propellant Rocket Engines written by Dieter K. Huzel and published by AIAA. This book was released on 1992 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:
