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 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 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 Monthly Catalog of United States Government Publications written by and published by . This book was released on 1999-07 with total page 1152 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 2005 with total page 432 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book Effects of Sidewall Geometry on the Installed Performance of Nonaxisymmetric Convergent divergent Exhaust Nozzles written by and published by . This book was released on 1980 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Several Geometric Parameters on the Static Internal Performance of Three Nonaxisymmetric Nozzle Concepts written by Bobby L. Berrier and published by . This book was released on 1979 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Internal Performance of a Nonaxisymmetric Nozzle with a Rotating Upper Flap and a Center pivoted Lower Flap written by David J. Wing and published by . This book was released on 1993 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Effect of Throat Contouring on Two dimensional Converging diverging Nozzles at Static Conditions written by Mary L. Mason and published by . This book was released on 1980 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book The Effect of Throat Contouring on Two dimensional Converging diverging Nozzles at Static Conditions written by Mary L. Mason and published by . This book was released on 1980 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Several Geometric Variables on Internal Performance of Short Convergent divergent Exhaust Nozzles written by Fred W. Steffen and published by . This book was released on 1955 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects on internal performance of several geometric variables that were intended to produce a short, high-performance convergent-divergent nozzle. It was found that shortening the convergent section by either changing its shape or decreasing the throat-contour radius had no effect on thrust coefficient. It was also found that a nozzle with a short conical divergent section had a higher thrust coefficient than a nozzle with either a stepped or contoured divergent section of approximately equal length.

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 Effect of Nozzle Inlet Geometry on Performance of a Swiveled Convergent divergent Nozzle written by Albert J. Pavli and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of Sidewall Geometry Effects on the Installed Performance of Nonaxisymmetric Convergent divergent Exhaust Nozzles written by Jeffrey A. Yetter and published by . This book was released on 1979 with total page 326 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