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Static Performance Of A Fixed Geometry Exhaust Nozzle Incorporating Porous Cavities For Shock Boundary Layer Interaction Control
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Book Synopsis Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control by : Scott C. Asbury
Download or read book Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control written by Scott C. Asbury and published by . This book was released on 1999 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721081639 Total Pages :140 pages Book Rating :4.0/5 (816 download)
Book Synopsis Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control by : National Aeronautics and Space Administration (NASA)
Download or read book Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control 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 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the model preparation area of the Langley 16-Foot Transonic Tunnel to determine the internal performance of a fixed-geometry exhaust nozzle incorporating porous cavities for shock-boundary layer interaction control. Testing was conducted at static conditions using a sub-scale nozzle model with one baseline and 27 porous configurations. For the porous configurations, the effects of percent open porosity, hole diameter, and cavity depth were determined. All tests were conducted with no external flow at nozzle pressure ratios from 1.25 to approximately 9.50. Results indicate that baseline nozzle performance was dominated by unstable, shock-induced, boundary-layer separation at over-expanded conditions. Porous configurations were capable of controlling off-design separation in the nozzle by either alleviating separation or encouraging stable separation of the exhaust flow. The ability of the porous nozzle concept to alternately alleviate separation or encourage stable separation of exhaust flow through shock-boundary layer interaction control offers tremendous off-design performance benefits for fixed-geometry nozzle installations. In addition, the ability to encourage separation on one divergent flap while alleviating it on the other makes it possible to generate thrust vectoring using a fixed-geometry nozzle. Asbury, Scott C. and Hunter, Craig A. Langley Research Center RTOP 538-14-12-01
Book Synopsis NASA Langley Scientific and Technical Information Output: 1999 by :
Download or read book NASA Langley Scientific and Technical Information Output: 1999 written by and published by . This book was released on 2000 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 2000 with total page 768 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 1963 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 10-13 July 2005, Tucson, Arizona: 05-4150 - 05-4199 by :
Download or read book 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 10-13 July 2005, Tucson, Arizona: 05-4150 - 05-4199 written by and published by . This book was released on 2005 with total page 714 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research and Technology Highlights, 1993 by :
Download or read book Research and Technology Highlights, 1993 written by and published by . This book was released on 1994 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit by :
Download or read book 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit written by and published by . This book was released on 1998 with total page 636 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle by : Scott C. Asbury
Download or read book Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle written by Scott C. Asbury and published by . This book was released on 1999 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent by : Eleanor Costilow Guentert
Download or read book Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent written by Eleanor Costilow Guentert and published by . This book was released on 1959 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of Several Method-of-characteristics Exhaust Nozzles by : John M. Farley
Download or read book Performance of Several Method-of-characteristics Exhaust Nozzles written by John M. Farley and published by . This book was released on 1960 with total page 38 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 1994 with total page 1036 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1.27 to 2.75 by : Paige B. Burbank
Download or read book The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1.27 to 2.75 written by Paige B. Burbank and published by . This book was released on 1951 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of designing an aymmetric, fixed-geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was a constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.02 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Book Synopsis Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent by : Eleanor Costilow Guentert
Download or read book Design of Axisymmetric Exhaust Nozzles by Method of Characteristics Incorporating a Variable Isentropic Exponent written by Eleanor Costilow Guentert and published by . This book was released on 1959 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical method for including thermodynamic data with variable isentropic exponent in the method of characteristics as applied to the design of high-temperature exhaust nozzles has been obtained. Several bell-shaped nozzles have been designed with this method. A comparison of nozzle contours obtained by assuming identical boundary conditions and either frozen or equilibrium composition shows that significant differences occur. A computation of the variation of vacuum specific impulse with axial length showed that considerable nozzle length, and hence weight, can be eliminated without serious thrust penalties in nozzle designs that gradually expand the flow to uniform exit conditions.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721002986 Total Pages :74 pages Book Rating :4.0/5 (29 download)
Book Synopsis Static Aerodynamic Performance Investigation of a Fluid Shield Nozzle by : National Aeronautics and Space Administration (NASA)
Download or read book Static Aerodynamic Performance Investigation of a Fluid Shield Nozzle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: In pursuit of an acoustically acceptable, high performance exhaust system capable of meeting Federal Aviation Regulation 36 Stage 3 noise goals for the High Speed Civil Transport application, General Electric Aircraft Engines conducted a design study to incorporate a fluid shield into a 36-chute suppressor exhaust-nozzle system. After a full scale preliminary mechanical design of the resulting fluid shield exhaust system, scale model aerodynamic performance tests and acoustic tests were conducted to establish both aerodynamic performance and acoustic characteristics. Data are presented as thrust coefficients, discharge coefficients, chute-base pressure drags, and plug static pressure distributions.Balan, C. and Askew, J. W.Glenn Research CenterCIVIL AVIATION; EXHAUST NOZZLES; AERODYNAMIC CHARACTERISTICS; AIRCRAFT ENGINES; MECHANICAL ENGINEERING; SHIELDING; FLUID FLOW; STATIC PRESSURE; DATA REDUCTION; THRUST; PLUGS; PRESSURE DISTRIBUTION; NOZZLE FLOW; NOISE REDUCTION
Book Synopsis Thrust Performance of a Variable-geometry, Nonaxisymmetric, Two-dimensional, Convergent-divergent Exhaust Nozzle on a Turbojet Engine at Altitude by : David M. Straight
Download or read book Thrust Performance of a Variable-geometry, Nonaxisymmetric, Two-dimensional, Convergent-divergent Exhaust Nozzle on a Turbojet Engine at Altitude written by David M. Straight and published by . This book was released on 1983 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Sidewall Geometry on the Installed Performance of Nonaxisymmetric Convergent-divergent Exhaust Nozzles by : Jeffery A. Yetter
Download or read book Effects of Sidewall Geometry on the Installed Performance of Nonaxisymmetric Convergent-divergent Exhaust Nozzles written by Jeffery A. Yetter and published by . This book was released on 1980 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
