Download or read book Simulation Model Development for Icing Effects Flight Training 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 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A high-fidelity simulation model for icing effects flight training was developed from wind tunnel data for the DeHavilland DHC-6 Twin Otter aircraft. First, a flight model of the un-iced airplane was developed and then modifications were generated to model the icing conditions. The models were validated against data records from the NASA Twin Otter Icing Research flight test program with only minimal refinements being required. The goals of this program were to demonstrate the effectiveness of such a simulator for training pilots to recognize and recover from icing situations and to establish a process for modeling icing effects to be used for future training devices. Barnhart, Billy P. and Dickes, Edward G. and Gingras, David R. and Ratvasky, Thomas P. Glenn Research Center NASA/TM-2003-212115, E-13767, NAS 1.15:212115, SAE-2002-01-1527

Download or read book Overview of Mount Washington Icing Sensors Project 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 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA, the FAA, the Department of Defense, the National Center for Atmospheric Research and NOAA are developing techniques for retrieving cloud microphysical properties from a variety of remote sensing technologies. The intent is to predict aircraft icing conditions ahead of aircraft. The Mount Washington Icing Sensors Project MWISP), conducted in April, 1999 at Mt. Washington, NH, was organized to evaluate technologies for the prediction of icing conditions ahead of aircraft in a natural environment, and to characterize icing cloud and drizzle environments. April was selected for operations because the Summit is typically in cloud, generally has frequent freezing precipitation in spring, and the clouds have high liquid water contents. Remote sensing equipment, consisting of radars, radiometers and a lidar, was placed at the base of the mountain, and probes measuring cloud particles, and a radiometer, were operated from the Summit. NASA s Twin Otter research aircraft also conducted six missions over the site. Operations spanned the entire month of April, which was dominated by wrap-around moisture from a low pressure center stalled off the coast of Labrador providing persistent upslope clouds with relatively high liquid water contents and mixed phase conditions. Preliminary assessments indicate excellent results from the lidar, radar polarimetry, radiosondes and summit and aircraft measurements. Ryerson, Charles C. and Politovich, Marcia K. and Rancourt, Kenneth L. and Koenig, George G. and Reinking, Roger F. and Miller, Dean R. Glenn Research Center NASA/TM-2003-212453, E-13961, NAS 1.15:212453, AIAA Paper 2000-0488

Download or read book Icing Cloud Calibration of the NASA Glenn Icing Research Tunnel written by Robert F. Ide and published by . This book was released on 2001 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The icing research tunnel at the NASA Glenn Research Center underwent a major rehabilitation in 1999, necessitating recalibration of the icing clouds. This report describes the methods used in the recalibration, including the procedure used to establish a uniform icing cloud and the use of a standard icing blade technique for measurement of liquid water content. The instruments and methods used to perform the droplet size calibration are also described. The liquid water content/droplet size operating envelopes of the icing tunnel are shown for a range of airspeeds and compared to the FAA icing certification criteria. The capabilities of the IRT to produce large droplet icing clouds is also detailed.

Download or read book We Freeze to Please a History of NASA s Icing Research Tunnel and the Quest for Flight Safety NASA SP 2002 4226 written by World Spaceflight News and published by . This book was released on 2017-08-20 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: This official NASA history document is a comprehensive account of NASA research on aircraft icing, a major threat to air safety. From the preface: Icing research has received only limited attention from historians. Yet the problem of icing has challenged aviators and aircraft manufacturers since the earliest days of powered flight-and continues to do so. At various times in the past, victory has been declared over the menace of icing, but these claims have always proved premature. Despite more than seven decades of research into the phenomena, much remains to be learned about the nature of icing and how best to respond to it. In the United States, the National Advisory Committee for Aeronautics (NACA) and its successor, the National Aeronautics and Space Administration (NASA), have led the way in investigating the interaction between aircraft and the icing environment, as well as in developing various means to protect fixed- and rotary-wing machines. To be sure, icing research has never been given a high priority. When the NACA began to investigate icing during the 1930s, most of the engineers at the Langley Memorial Aeronautical Laboratory were far more interested in advances in aerodynamics than they were in icing. When work shifted to the new Aircraft Engine Research Laboratory in Cleveland in the 1940s, icing research represented only a minor interest of a laboratory that was devoted to engine development. Later, the demands of the space age overshadowed NASA's work on aeronautics. Within this limited context, icing investigations usually ranked low on the aeronautical research agenda. Perhaps because of their lack of status in the NACA/NASA world, icing researchers tended to form a close-knit group. Untroubled by distinctions between fundamental research and practical engineering, they believed that they were doing important work and were making a significant contribution to safety. They found other icing enthusiasts in industry, academia, and government agencies, both in the United States and abroad, and eventually came together in an international "icing community." In telling the story of NACA/NASA icing research, I have focused on the role of the Icing Research Tunnel (IRT) at the Cleveland laboratory. Because the experiments that were conducted in the IRT formed only part of a broader investigation into icing which encompassed flight research and computer simulation, I have included information about these topics while keeping the tunnel at the center of my study. Also, I have attempted to place the work of the NACA/NASA in the broader context of the icing problems faced by the international aviation community. The dangers posed by icing rarely concerned aviators during the first two decades of powered flight. Lacking the instruments necessary to fly without visual references, pilots did their best to avoid clouds. As a result, encounters with icing seldom happened and were always inadvertent. The situation changed in the mid-1920s when the intrepid aviators of the U.S. Air Mail Service attempted to maintain scheduled day-and-night operations between New York and Chicago. These instrument-flying pioneers were the first group of flyers to face the icing menace on a regular basis. As one of their pilots noted at the time about the hazards of the New York-Chicago route, "the greatest of all our problems is ice."

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 An Experimental and Numerical Study of Icing Effects on the Performance and Controllability of a Twin Engine Aircraft written by Andrew L. Reehorst and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Survey of Aircraft Icing Simulation Test Facilities in North America written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-06 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A survey was made of the aircraft icing simulation facilities in North America: there are 12 wind tunnels, 28 engine test facilities, 6 aircraft tankers and 14 low velocity facilities, that perform aircraft icing tests full or part time. The location and size of the facility, its speed and temperature range, icing cloud parameters, and the technical person to contact are surveyed. Results are presented in tabular form. The capabilities of each facility were estimated by its technical contact person. The adequacy of these facilities for various types of icing tests is discussed. Olsen, W. Glenn Research Center NASA-TM-81707, E-736 RTOP 505-44-12

Download or read book Mixed Phase Icing Simulation and Testing at the Cox Icing Wind Tunnel 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 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new capability was developed for indoor simulation of snow and mixed-phase icing conditions. This capability is useful for year-round testing in the Cox closed-loop Icing Wind Tunnel. Certification of aircraft for flight into these types of icing conditions is only required by the JAA in Europe. In an effort to harmonize certification requirements, the FAA in the US sponsored a preliminary program to study the effects of mixed-phase and fully glaciated icing conditions on the performance requirements of thermal ice protection systems. This paper describes the test program and the associated results. Al-Khalil, Kamel and Irani, Eddie and Miller, Dean Glenn Research Center NASA/TM-2003-212395, E-13978, NAS 1.15:212395, AIAA Paper 2003-0903

Download or read book Preliminary Results from a Heavily Instrumented Engine Ice Crystal Icing Test in a Ground Based Altitude Test Facility written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Preliminary results from the heavily instrumented ALF502R-5 engine test conducted in the NASA Glenn Research Center Propulsion Systems Laboratory are discussed. The effects of ice crystal icing on a full scale engine is examined and documented. This same model engine, serial number LF01, was used during the inaugural icing test in the Propulsion Systems Laboratory facility. The uncommanded reduction of thrust (rollback) events experienced by this engine in flight were simulated in the facility. Limited instrumentation was used to detect icing on the LF01 engine. Metal temperatures on the exit guide vanes and outer shroud and the load measurement were the only indicators of ice formation. The current study features a similar engine, serial number LF11, which is instrumented to characterize the cloud entering the engine, detect/characterize ice accretion, and visualize the ice accretion in the region of interest. Data were acquired at key LF01 test points and additional points that explored: icing threshold regions, low altitude, high altitude, spinner heat effects, and the influence of varying the facility and engine parameters. For each condition of interest, data were obtained from some selected variations of ice particle median volumetric diameter, total water content, fan speed, and ambient temperature. For several cases the NASA in-house engine icing risk assessment code was used to find conditions that would lead to a rollback event. This study further helped NASA develop necessary icing diagnostic instrumentation, expand the capabilities of the Propulsion Systems Laboratory, and generate a dataset that will be used to develop and validate in-house icing prediction and risk mitigation computational tools. The ice accretion on the outer shroud region was acquired by internal video cameras. The heavily instrumented engine showed good repeatability of icing responses when compared to the key LF01 test points and during day-to-day operation. Other noticeable observations are presented. Flegel, Ashlie B. and Oliver, Michael J. Glenn Research Center ALTITUDE TESTS; ENGINE TESTS; ICE FORMATION; AIRCRAFT ICING; MOISTURE CONTENT; RISK ASSESSMENT; TEMPERATURE EFFECTS; TEST FACILITIES; PROPULSION SYSTEM PERFORMANCE; LOW ALTITUDE; HIGH ALTITUDE; RESEARCH FACILITIES

Download or read book Dra Nasa Onera Collaboration on Icing Research Part 2 Prediction of Airfoil Ice Accretion written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents results from a joint study by DRA, NASA, and ONERA for the purpose of comparing, improving, and validating the aircraft icing computer codes developed by each agency. These codes are of three kinds: (1) water droplet trajectory prediction, (2) ice accretion modeling, and (3) transient electrothermal deicer analysis. In this joint study, the agencies compared their code predictions with each other and with experimental results. These comparison exercises were published in three technical reports, each with joint authorship. DRA published and had first authorship of Part 1 - Droplet Trajectory Calculations, NASA of Part 2 - Ice Accretion Prediction, and ONERA of Part 3 - Electrothermal Deicer Analysis. The results cover work done during the period from August 1986 to late 1991. As a result, all of the information in this report is dated. Where necessary, current information is provided to show the direction of current research. In this present report on ice accretion, each agency predicted ice shapes on two dimensional airfoils under icing conditions for which experimental ice shapes were available. In general, all three codes did a reasonable job of predicting the measured ice shapes. For any given experimental condition, one of the three codes predicted the general ice features (i.e., shape, impingement limits, mass of ice) somewhat better than did the other two. However, no single code consistently did better than the other two over the full range of conditions examined, which included rime, mixed, and glaze ice conditions. In several of the cases, DRA showed that the user's knowledge of icing can significantly improve the accuracy of the code prediction. Rime ice predictions were reasonably accurate and consistent among the codes, because droplets freeze on impact and the freezing model is simple. Glaze ice predictions were less accurate and less consistent among the codes, because the freezing model is more complex and is critically dependent...

Download or read book Aircraft Icing written by and published by . This book was released on 1978 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt: Icing of unprotected aircraft components is a major problem engineers are faced with during the development phase of an aircraft programme. Ice accretions as well as their shape have to be predicted in order to investigate their effect on aerodynamic flight safety and performance and to decide on the need for anti-or de-icing systems. The Fluid Dynamics Panel of AGARD sponsored a round-table discussion on the subject of Aircraft Icing, on 30 September 1977, in Ottawa, Canada, in conjunction with an FDP Symposium on Unsteady Aerodynamics. The seven papers presented, covering a broad spectrum of topics, are presented in this Advisory Report. (Author).

Download or read book Evaluation of Ncar Icing Sld Forecasts Tools and Techniques Used During the 1998 NASA Sld Flight Season written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-19 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supercooled Large Droplet (SLD) icing conditions were implicated in at least one recent aircraft crash, and have been associated with other aircraft incidents. Inflight encounters with SLD can result in ice accreting on unprotected areas of the wing where it can not be removed. Because this ice can adversely affect flight characteristics of some aircraft, there has been concern about flight safety in these conditions. The FAA held a conference on in-flight icing in 1996 where the state of knowledge concerning SLD was explored. One outcome of these meetings was an identified need to acquire SLD flight research data, particularly in the Great Lakes Region. The flight research data was needed by the FAA to develop a better understanding of the meteorological characteristics associated with SLD and facilitate an assessment of existing aircraft icing certification regulations with respect to SLD. In response to this need, NASA, the Federal Aviation Administration (FAA), and the National Center for Atmospheric Research (NCAR) conducted a cooperative icing flight research program to acquire SLD flight research data. The NASA Glenn Research Center's Twin Otter icing research aircraft was flown throughout the Great Lakes region during the winters of 1996-97 and 1997-98 to acquire SLD icing and meteorological data. The NASA Twin Otter was instrumented to measure cloud microphysical properties (particle size, LWC (Liquid Water Content), temperature, etc.), capture images of wing and tail ice accretion, and then record the resultant effect on aircraft performance due to the ice accretion. A satellite telephone link enabled the researchers onboard the Twin Otter to communicate with NCAR meteorologists. who provided real-time guidance into SLD icing conditions. NCAR meteorologists also provided preflight SLD weather forecasts that were used to plan the research flights, and served as on-board researchers. This document contains an evaluation of the tools and techniques NCAR forec

Download or read book NASA FAA Tailplane Icing Program written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2020-06-30 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents results from research flights that explored the characteristics of an ice-contaminated tailplane using various simulated ice shapes attached to the leading edge of the horizontal tailplane. A clean leading edge provided the baseline case, then three ice shapes were flown in order of increasing severity. Flight tests included both steady state and dynamic maneuvers. The steady state points were 1G wings level and steady heading sideslips. The primary dynamic maneuvers were pushovers to various G-levels; elevator doublets; and thrust transitions. These maneuvers were conducted for a full range of flap positions and aircraft angle of attack where possible. The analysis of this data set has clearly demonstrated the detrimental effects of ice contamination on aircraft stability and controllability. Paths to tailplane stall were revealed through parameter isolation and transition studies. These paths are (1) increasing ice shape severity, (2) increasing flap deflection, (3) high or low speeds, depending on whether the aircraft is in a steady state (high speed) or pushover maneuver (low speed), and (4) increasing thrust. The flight research effort was very comprehensive, but did not examine effects of tailplane design and location, or other aircraft geometry configuration effects. However, this effort provided the role of some of the parameters in promoting tailplane stall. The lessons learned will provide guidance to regulatory agencies, aircraft manufacturers, and operators on ice-contaminated tailplane stall in the effort to increase aviation safety and reduce the fatal accident rate. Ratvasky, Thomas P. and VanZante, Judith Foss and Sim, Alex Armstrong Flight Research Center; Glenn Research Center NASA/TP-2000-209908, NAS 1.60:209908, DOT/FAA/AR-99/85, E-12126 DTFA03-95-90001; RTOP 548-21-23 36586 AIRCRAFT ICING; HORIZONTAL TAIL SURFACES; AIRCRAFT STABILITY; LEADING EDGES; FLIGHT TESTS; AIRCRAFT SAFETY; CONTROLLABILITY; FLAPPING; WINGS; THRUST; FLIGHT HAZARDS; ICE PREVENTION

Download or read book Nasa FAA Tailplane Icing Program written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents results from research flights that explored the characteristics of an ice-contaminated tailplane using various simulated ice shapes attached to the leading edge of the horizontal tailplane. A clean leading edge provided the baseline case, then three ice shapes were flown in order of increasing severity. Flight tests included both steady state and dynamic maneuvers. The steady state points were 1G wings level and steady heading sideslips. The primary dynamic maneuvers were pushovers to various G-levels; elevator doublets; and thrust transitions. These maneuvers were conducted for a full range of flap positions and aircraft angle of attack where possible. The analysis of this data set has clearly demonstrated the detrimental effects of ice contamination on aircraft stability and controllability. Paths to tailplane stall were revealed through parameter isolation and transition studies. These paths are (1) increasing ice shape severity, (2) increasing flap deflection, (3) high or low speeds, depending on whether the aircraft is in a steady state (high speed) or pushover maneuver (low speed), and (4) increasing thrust. The flight research effort was very comprehensive, but did not examine effects of tailplane design and location, or other aircraft geometry configuration effects. However, this effort provided the role of some of the parameters in promoting tailplane stall. The lessons learned will provide guidance to regulatory agencies, aircraft manufacturers, and operators on ice-contaminated tailplane stall in the effort to increase aviation safety and reduce the fatal accident rate. Ratvasky, Thomas P. and VanZante, Judith Foss and Sim, Alex Armstrong Flight Research Center; Glenn Research Center DTFA03-95-90001; RTOP 548-21-23

Download or read book Initial Flight Test of the Production Support Flight Control Computers at NASA Dryden Flight Research Center written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Dryden Flight Research Center has completed the initial flight test of a modified set of F/A-18 flight control computers that gives the aircraft a research control law capability. The production support flight control computers (PSFCC) provide an increased capability for flight research in the control law, handling qualities, and flight systems areas. The PSFCC feature a research flight control processor that is "piggybacked" onto the baseline F/A-18 flight control system. This research processor allows for pilot selection of research control law operation in flight. To validate flight operation, a replication of a standard F/A-18 control law was programmed into the research processor and flight-tested over a limited envelope. This paper provides a brief description of the system, summarizes the initial flight test of the PSFCC, and describes future experiments for the PSFCC. Carter, John and Stephenson, Mark Armstrong Flight Research Center NASA/TM-1999-206581, H-2343, NAS 1.15:206581, AIAA Paper 99-4203