An Experimental Study of Flow in a Nozzle Designed to Provide a Parallel Jet at Supersonic Speed PDF Download
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Author: Thomas Vincent Hennessey
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Author: Thomas Vincent Hennessey
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Author: Thomas V. Hennessey
Publisher:
ISBN:
Category :
Languages : en
Pages : 92
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Author:
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ISBN:
Category : Engineering
Languages : en
Pages : 502
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Author:
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ISBN:
Category : Engineering
Languages : en
Pages : 842
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723836725
Category : Science
Languages : en
Pages : 50
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Book Description
An experimental and computational study was conducted on a high-speed, single-expansion-ramp nozzle (SERN) concept designed for efficient off-design performance. The translating-throat SERN concept adjusts the axial location of the throat to provide a variable expansion ratio and allow a more optimum jet exhaust expansion at various flight conditions in an effort to maximize nozzle performance. Three design points (throat locations) were investigated to simulate the operation of this concept at subsonic-transonic, low supersonic, and high supersonic flight conditions. The experimental study was conducted in the jet exit test facility at the Langley Research Center. Internal nozzle performance was obtained at nozzle pressure ratios (NPR's) up to 13 for six nozzles with design nozzle pressure ratios near 9, 42, and 102. Two expansion-ramp surfaces, one concave and one convex, were tested for each design point. Paint-oil flow and focusing schlieren flow visualization techniques were utilized to acquire additional flow data at selected NPR'S. The Navier-Stokes code, PAB3D, was used with a two-equation k-e turbulence model for the computational study. Nozzle performance characteristics were predicted at nozzle pressure ratios of 5, 9, and 13 for the concave ramp, low Mach number nozzle and at 10, 13, and 102 for the concave ramp, high Mach number nozzle.Deere, Karen A. and Asbury, Scott C.Langley Research CenterNAVIER-STOKES EQUATION; THROATS; EXHAUST NOZZLES; NOZZLE DESIGN; COMPUTATIONAL FLUID DYNAMICS; K-EPSILON TURBULENCE MODEL; NOZZLE EFFICIENCY; FLOW VISUALIZATION; TRANSONIC FLIGHT; SUPERSONIC FLIGHT; SCHLIEREN PHOTOGRAPHY
Author: Gerald M. Mulenburg
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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This study is an experimental evaluation of the performance of 12 two-dimensional, converging-diverging, cold flow, supersonic nozzles, each with the same throat and divergent section. The relative efficiency of each nozzle was evaluated by a comparison of total pressure measurements taken in the exit plane, schlieren photographs of the flow, and heat transfer characteristics using moire' patterns. The nozzle with the highest efficiency had an inlet which was an ellipse faired to a 45 degree ramp. Its performance was closely followed by that of a nozzle with a circular arc inlet having a radius of three times the throat height. The three nozzles with the lowest efficiencies were those with 30, 45, and 60 degrees linear ramp inlets, respectively. The results of this study indicate that, in nozzle design, a region of immense importance is the curvature just prior to the throat and how this curvature is joined to the throat section. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Author:
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ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 568
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 522
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 580
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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
