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:
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
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 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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:
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 900 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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:
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:
Download or read book Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed Geometry Nonaxisymmetric Exhaust Nozzle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-30 with total page 76 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 effects of convoluted divergent-flap contouring on the internal performance of a fixed-geometry, nonaxisymmetric, convergent-divergent exhaust nozzle. Testing was conducted at static conditions using a sub-scale nozzle model with one baseline and four convoluted configurations. 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 overexpanded conditions. Convoluted configurations were found to significantly reduce, and in some cases totally alleviate separation at overexpanded conditions. This result was attributed to the ability of convoluted contouring to energize and improve the condition of the nozzle boundary layer. Separation alleviation offers potential for installed nozzle aeropropulsive (thrust-minus-drag) performance benefits by reducing drag at forward flight speeds, even though this may reduce nozzle thrust ratio as much as 6.4% at off-design conditions. At on-design conditions, nozzle thrust ratio for the convoluted configurations ranged from 1% to 2.9% below the baseline configuration; this was a result of increased skin friction and oblique shock losses inside the nozzle.Asbury, Scott C. and Hunter, Craig A.Langley Research CenterCONVERGENT-DIVERGENT NOZZLES; BOUNDARY LAYER SEPARATION; WIND TUNNEL NOZZLES; WIND TUNNEL TESTS; NOZZLE FLOW; OBLIQUE SHOCK WAVES; FLOW VISUALIZATION; NOZZLE GEOMETRY; AERODYNAMIC DRAG; SKIN FRICTION; PRESSURE RATIO; FLAPS (CONTROL SURFACES)
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:
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:
Download or read book An Approximate Theoretical Method for Modeling the Static Thrust Performance of Non axisymmetric Two dimensional Convergent divergent Nozzles written by and published by . This book was released on 1995 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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
Download or read book An Improved Interaction Method for Calculating Exhaust Nozzle Boattail Flows written by Gary D.. Kuhn and published by . This book was released on 1980 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Current Papers written by and published by . This book was released on 1950 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
