Download or read book Collection Efficiency and Ice Accretion Characteristics of Two Full Scale and One 1 4 Scale Business Jet Horizontal Tails written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Collection efficiency and ice accretion calculations have been made for a series of business jet horizontal tail configurations using a three-dimensional panel code, an adaptive grid code, and the NASA Glenn LEWICE3D grid based ice accretion code. The horizontal tail models included two full scale wing tips and a 25 percent scale model. Flow solutions for the horizontal tails were generated using the PMARC panel code. Grids used in the ice accretion calculations were generated using the adaptive grid code ICEGRID. The LEWICE3D grid based ice accretion program was used to calculate impingement efficiency and ice shapes. Ice shapes typifying rime and mixed icing conditions were generated for a 30 minute hold condition. All calculations were performed on an SGI Octane computer. The results have been compared to experimental flow and impingement data. In general, the calculated flow and collection efficiencies compared well with experiment, and the ice shapes appeared representative of the rime and mixed icing conditions for which they were calculated.Bidwell, Colin S. and Papadakis, MichaelGlenn Research CenterHORIZONTAL TAIL SURFACES; SCALE MODELS; FULL SCALE TESTS; AIRCRAFT ICING; COMPUTATIONAL FLUID DYNAMICS; WIND TUNNEL TESTS; JET AIRCRAFT; PANEL METHOD (FLUID DYNAMICS); WING TIPS; DATA SYSTEMS; THREE DIMENSIONAL FLOW; JET IMPINGEMENT

Download or read book Collection Efficiency and Ice Accretion Characteristics of Two Full Scale and One 1 4 Scale Business Jet Horizontal Tails written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Collection efficiency and ice accretion calculations have been made for a series of business jet horizontal tail configurations using a three-dimensional panel code, an adaptive grid code, and the NASA Glenn LEWICE3D grid based ice accretion code. The horizontal tail models included two full scale wing tips and a 25 percent scale model. Flow solutions for the horizontal tails were generated using the PMARC panel code. Grids used in the ice accretion calculations were generated using the adaptive grid code ICEGRID. The LEWICE3D grid based ice accretion program was used to calculate impingement efficiency and ice shapes. Ice shapes typifying rime and mixed icing conditions were generated for a 30 minute hold condition. All calculations were performed on an SGI Octane computer. The results have been compared to experimental flow and impingement data. In general, the calculated flow and collection efficiencies compared well with experiment, and the ice shapes appeared representative of the rime and mixed icing conditions for which they were calculated.

Download or read book Sustainable Aviation written by T. Hikmet Karakoc and published by Springer. This book was released on 2016-07-20 with total page 413 pages. Available in PDF, EPUB and Kindle. Book excerpt: This expansive reference on the use of clean energy technologies in the aviation industry focuses on tools and solutions for maximizing the energy efficiency of aircrafts, airports, and other auxiliary components of air transit. Key topics range from predicting impacts of avionics and control systems to energy/exergy performance analyses of flight mechanics and computational fluid dynamics. The book includes findings both from experimental investigations and functional extant systems, ranging from propulsion technologies for aerospace vehicles to airport design to energy recovery systems. Engineers, researchers and students will benefit from the broad reach and numerous engineering examples provided.

Download or read book Proceedings etc2016 written by AMA Service GmbH and published by BoD – Books on Demand. This book was released on 2016-09-28 with total page 253 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the second time the European Telemetry and Test Conference – etc2016 took place from 10 – 12 May 2016 in Nuremberg (Germany), in collaboration with the SENSOR+TEST 2016. Worldwide, there is no comparable platform to SENSOR+TEST / etc that offers such an intensive innovation dialog between suppliers of sensors, measuring and testing technology and users from all major industries. This cooperation provides in addition etc2016 exhibitors the opportunity to meet international customers from industry, science and research – from automotive industries, machinery constructions, electrical and energy industry, and of course aviation and space. The etc2016 spotlights the most recent innovations in methods, systems, and instrumentation from industry, researchers and laboratories all around the world. The European Telemetry and Test Conference offers original technical papers and innovation ideas in Test, Telemetry, Telecontrol, Instrumentation and Recording technologies for industrial, automotive, scientific, aerospace, space, naval and military applications.

Download or read book Annual Index abstracts of Sae Technical Papers 2000 written by Society Of Automotive Engineers and published by . This book was released on 2001 with total page 868 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Ice Accretion Prediction for a Typical Commercial Transport Aircraft written by C. S. Bidwell and published by . This book was released on 1993 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Collection Efficiency and Ice Accretion Calculations for a Sphere a Swept MS 1 317 Wing a Swept NACA 0012 Wing Tip an Axisymmetric Inlet and a Boeing 737 300 written by and published by . This book was released on 1995 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Ice Accretion Calculations for a Commercial Transport Using the LEWICE3D ICEGRID3D and CMARC Programs written by C. Bidwell and published by . This book was released on 1999 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Collection Efficiency and Ice Accretion Calculations for a Boeing 737 300 Inlet written by Colin S. Bidwell and published by . This book was released on 1997 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 40th AIAA Aerospace Sciences Meeting Exhibit written by and published by . This book was released on 2002 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Collection Efficiency and Ice Accretion Calculations for a Sphere a Swept MS 1 317 Wing a Swept NACA 0012 Wing Tip an Axisymmetric Inlet and a Boeing 737 300 Inlet written by C. S. Bidwell and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Analysis and Verification of the Icing Scaling Equations Volume 1 Revision written by Gary A. Ruff and published by . This book was released on 1986 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Study objectives were to evaluate the equations governing the ice-accretion process to identify proposed scaling parameters and to conduct tests to determine which, is any, of the proposed methods produced scale ice accretions. Study results include: (1) A set of equations that can be used to calculate test conditions so that scaled ice shapes are produced on geometrically similar bodies was developed and experimentally verified. (2) Posttest evaluation of the scaling parameters based on the actual test conditions was necessary for accurate evaluation of test results. (3) An icing similitude computer code, SIMICE, was developed to calculate similtude conditions using the verified scaling equations. (4) The equations were applicable over the range of meteorological conditions found in natural icing, with the possible exception of velocity. (5) Velocity is the primary limitation of the scaling equations. To maintain scaled flow fields and droplet impingement characteristics, both the model and full-scale velocities must yield a Reynolds number> or = 200,000 and

Download or read book Experimental Ice Shape and Performance Characteristics for a Multi Element Airfoil in the NASA Lewis Icing Research Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-24 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study of the ice accretion patterns and performance of characteristics of a multi-element airfoil was undertaken at the NASA-Lewis Icing Research Tunnel. Several configurations were examined to determine the ice shape and performance characteristics. The testing included glaze, rime, and mixed icing regimes. Tunnel cloud conditions were set to correspond to those typical of the operating environment for commercial transport aircraft. Measurements acquired included ice profile tracings and aerodynamic forces both during the accretion process and in a post-accretion evaluation over a range of angle of attack. Substantial ice accretions developed on the main wing, flaps, and slat surfaces. Force measurements indicate severe performance degradation, especially near CL max, for both light and heavy ice accretion. Frost was seen on the lower surface of the airfoil which was found to contribute significantly to the force components. Berkowitz, Brian M. and Potapczuk, Mark G. and Namdar, Bahman S. and Langhals, Tammy J. Glenn Research Center NASA-TM-105380, E-6767, NAS 1.15:105380 NAS3-25266; RTOP 505-68-10...

Download or read book Quantification of Ice Accretions for Icing Scaling Evaluations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The comparison of ice accretion characteristics is an integral part of aircraft icing research. It is often necessary to compare an ice accretion obtained from a flight test or numerical simulation to one produced in an icing wind tunnel or for validation of an icing scaling method. Traditionally, this has been accomplished by overlaying two-dimensional tracings of ice accretion shapes. This paper addresses the basic question of how to compare ice accretions using more quantitative methods. For simplicity, geometric characteristics of the ice accretions are used for the comparison. One method evaluated is a direct comparison of the percent differences of the geometric measurements. The second method inputs these measurements into a fuzzy inference system to obtain a single measure of the goodness of the comparison. The procedures are demonstrated by comparing ice shapes obtained in the Icing Research Tunnel at NASA Glenn Research Center during recent icing scaling tests. The results demonstrate that this type of analysis is useful in quantifying the similarity of ice accretion shapes and that the procedures should be further developed by expanding the analysis to additional icing data sets. Ruff, Gary A. and Anderson, David N. Glenn Research Center NASA/TM-2003-212308, NAS 1.15:212308, E-13891, AIAA Paper 98-0195

Download or read book Full scale Runback Ice written by Nathalie Alegre and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The runback ice phenomenon is well-known for anti-icing or de-icing systemswhen the system is not evaporating 100% of the water impinging the surface. The water runs back to the point where the added heat no longer raisesthe surface temperature above freezing. The water freezes behind this limit. No runback ice is tolerated for some flight configurations, but not for all. Then for o.-design cases, some runback ice may grow on the wings surface. However, data from full-scale realistic runback ice is not very well-known byaircraft manufacturers and they are not sure what thickness is allowed beforethe e.ect of the ice on the flow becomes too adverse. To better understand full-scale high-fidelity runback ice growth and how itcan be simulated with simplistic shapes, test campaigns and CFD studieswere undertaken. First of all, tests in the Cranfield icing tunnel were performed. In this work, full-scale runback ice shapes were grown on a modelwith a full-scale leading edge equiped with an electrical heating system. Aninnovative moulding and casting technique has been introduced which allowedthe production of 3D planarised full-scale realistic runback ice castings. Inparallel to the icing tunnel tests, a mass and energy balance has been computedon Excel. This energy and mass balance can predict the heat andmass fluxes involved in the runback ice accretion mechanism. Following this, aerodynamic tests of the ice castings were lead in one of the low speed windtunnels at Cranfield University. The aerodynamics of simplistic shapes suchas geometrical shapes or ballotini layers were also studied. The e.ects of theice castings on the flow were compared to the e.ects of the simplistic shapes. The tests were done on a flat surface and not on an airfoil due to technicalcomplications. The boundary layer displacement thickness was the parameterused to quantify the e.ect of the shapes on the flow. 2D CFD simulationswere performed as a support to the testing but as well to compare with theexperimental data. The CFD simulations were for steady or unsteady flow. It has been possible to grow full-scale ice shapes in a relatively small icingtunnel. The shapes have been successfuly moulded and cast using siliconeand plaster mixed with polymer. A catalogue of runback ice shapes for differentliquid water content, heat inputs and positions along the chord hasbeen recorded. Following the wind tunnel tests, it has been possible to find arelationship between the real ice and the simplistic shapes. Thin runback iceshapes (4 mm) has a similar e.ect on the flow as a layer of 1 mm ballotini. It was found that thicker ice shapes, of the order of 1 cm, is equivalent to arectangle with rounded corner, associated with 1mm ballotini. The triangleshape which is usually used to simulate runback ice by the aircraft manufacturers, was found to be the most aerodynamically penalising simplisitc shapethat has been investigated in this PhD project. It was found that roundedcorners greatly improve the representativeness of the simplistic shapes, suchas triangle or rectangle.

Download or read book Aviation Weather for Pilots and Flight Operations Personnel written by United States. Federal Aviation Administration and published by . This book was released on 1975 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book International Aerospace Abstracts written by and published by . This book was released on 1984 with total page 698 pages. Available in PDF, EPUB and Kindle. Book excerpt: