Last edited by Malagul
Sunday, August 2, 2020 | History

2 edition of An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel found in the catalog.

An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel

An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel

  • 96 Want to read
  • 5 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Aircraft models.,
  • Data bases.,
  • Drops (Liquids),
  • Helicopters.,
  • Ice formation.,
  • Moisture content.,
  • Rotary wings.,
  • Rotar speed.,
  • Shafts (Machine elements),
  • Tip speed.

  • Edition Notes

    StatementRandall K. Britton, Thomas H. Bond and Robert J. Flemming.
    SeriesNASA technical memorandum -- 106471.
    ContributionsBritton, Randall K., Bond, Thomas H., Flemming, Robert J., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14708796M

    Numerical Modeling of Anti-icing Systems and Comparison to Test Results on a NACA Airfoil Kamel M. AI-Khalil* and Mark G. Potapczuk t NASA Lewis Research Center Cleveland, Ohio A series of experimental tests were conducted in the NASA Lewis IRT on an electro-thermally heated NACA airfoil. are not represented. Complete rotor icing studies can be undertaken in NASA Glenn’s Icing Research Tunnel (IRT), but model rotor diameters are limited to 6 ft by the test section (Ref. 13). Full scale studies may be accomplished with the Helicopter In-flight Spray System (HISS), but detailed icing shapes are difficult to acquire.

    The objective of this research project is divided in four parts: (1) to design a piezoelectric actuator-based de-icing system integrated to a flat plate experimental setup and develop a numerical model of the system with experimental validation, (2) use the experimental setup to investigate actuator activation with frequency sweeps and. Rotor icing is a serious threat to helicopter flight safety and computational fluid dynamics technology is very useful in icing prediction. In this work, a numerical simulation method is presented to calculate three-dimensional rotor icing in hovering flight. The rotor .

    While use of the SPC test chambers ground to a halt, the facility’s shop area was converted into an antenna test facility. In the early s, NASA considered restoring the facility to its wind tunnel configuration to address new areas of icing research. After several years of engineering analysis, Congress cancelled the effort. Wind Tunnel Test Results for a Shape Memory Alloy Based De-Icing System for Aircraft Regular Price: $ Member price: $ Anti-Icing Systems of Helicopter Rotor Blades Regular Price: $ Member price: $


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An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel Download PDF EPUB FB2

NASA Technical Reports Server (NTRS) An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel Item Preview. Get this from a library. An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel. [Randall K Britton; Thomas H Bond; Robert J Flemming; United States.

National Aeronautics and Space Administration.;]. Rotor icing testing can be accomplished in NASA Glenn's Icing Research Tunnel (IRT), but model rotor diameters are limited to 6 ft by the test section [1].

The Helicopter In-flight Spray System. An overview of a model rotor icing test in the NASA Lewis Icing Research Tunnel.

a heavily instrumented sub-scale model of a helicopter main rotor was tested in the NASA LeRC Icing Research Tunnel (IRT). The results of this series of tunnel tests were published previously.

After studying the results from the test and comparing them to.An overview of a model rotor icing test in the NASA lewis icing research tunnel,AIAA paper Flemming, R.J. and Lednicer, D.A., High speed ice accretion on rotor-craft airfoils,NASA CR Results of an icing test on a NACA airfoil in the NASA Lewis Icing Research Tunnel Article (PDF Available) February with Reads How we measure 'reads'.

Test Procedure 48 The Icing Research Tunnel 48 Comparison of Heat Transfer Model Results Summary of Ice Growth Behavior and Heat Transfer Characteristics 57 60 63 68 70 70 71 74 81 5. conditions in the NASA Lewis Icing Research Tunnel, and similarly for a cylinder exposed in flight to natural icing.

Icing tests were performed in the NASA Lewis Icing Research Tunnel (IRT) with cylinders ranging from to cm diameter. Reference conditions were chosen to provide rime, mixed and glaze ice.

The major facilities include a low-speed icing wind tunnel, a high-speed variable density tunnel, a refrigerated jet engine test cell, and a helicopter icing spray rig. 10 refs. View Show abstract.“ An Overview of a Model Rotor Icing Test in the NASA Lewis Icing Research Tunnel,” NASA TMLink Google Scholar [5] Britton R.

K., “ Ice Accretion Characteristics of a Model Rotor in the NASA Lewis Icing Research Tunnel,” AHS/SAE International Icing Symposium ‘95, Montreal, Oct. Google Scholar. InWhalen et al. [1] presented the results of a test program at the NASA Icing Research Tunnel to generate runback ice accretions on a fullscale model equipped with a hot-air anti-icing.

Glenn Research Center at Lewis Field 24 Icing Research Tunnel FLOW hp FAN VARICHRON DRIVE CONTROL ROOM TON COOLER ICING SPRAYS TURNING VANES Max Speed: m/s Test Section: x m BALANCE CHAMBER SECONDARY CONTROL ROOM T min = o C Capabilities: • Develop and test aircraft de-icing and anti-icing systems • MVDμ.

The Icing Branch at NASA Lewis Research Center (LeRC) surveyed the four major U.S. helicopter manufacturers to determine what type of information would be most helpful to obtain from a model rotor test in the Icing Research Tunnel (IRT). The specified industry needs were as follows: I) Time history of shedding during an icing encounter.

The Lewis Research Center's 6- by 9- by Foot Icing Research Tunnel, built inis the world's largest refrigerated tunnel for year-round use to examine protection systems against hazardous ice formations on wings, air inlets, rotors and V/STOL aircraft.

The largest wind tunnel in the world is at NASA's Ames Research Center. [13] Hauger H. and Englar K., “ Analysis of Model Testing in an Icing Wind Tunnel,” Douglas Aircraft Company, Inc. Rept. SM, May Google Scholar [14] Sibley E. and Smith R., “ Model Testing in an Icing Wind Tunnel,” Lockheed Aircraft Corp.

Rept. LR, MODEL ROTOR ICING TESTS IN THE NASA LEWIS ICING RESEARCH TUNNEL Robert J. Flemming Senior Design Engineer Sikorsky Aircraft Division, UTC Main Street Stratford, Connecticut USA Randall K.

Britton Icing Research Engineer Sverdrup Technology, Inc. NASA Lewis Research Center Group Aerospace Parkway Brookpark, Ohio USA. Insomething wholly unexpected happened at what was then the NASA Lewis (now Glenn) Research Center—a “new” aircraft icing program was started.

The story goes something like this: Milt Beheim, chief of the Wind Tunnel and Flight Division, was put in charge of the nearly defunct Icing Research Tunnel (IRT). It was in a state of. An experiment was conducted by the Helicopter Icing Consortium (HIC) in the NASA Lewis Icing Research Tunnel (IRT) in which a 1/6 scale fuselage model of a UHA Black Hawk helicopter with a generic rotor was subjected to a wide range of icing conditions.

1. Introduction. Helicopter rotor icing has been studied within the last 30 years. When ice forms on helicopter rotors, there is a large increase in required power and a large decrease of rotor lift.Safety concerns regarding rotor icing and the time consuming, high cost of flight tests have created great interest in numerical simulation investigations.

Design rules for damage tolerance from shed-ice impact are not well developed because of a lack of experimental data. Thus, NASA Lewis (LeRC) has begun an effort to develop a database of impact force and energy resulting from shed ice. This effort consisted of a test of NASA LeRC's Model Rotor Test Rig (MRTR) in the Icing Research Tunnel (IRT).

Icing experiments can be performed in an icing wind tunnel or a field test. Icing wind tunnel tests have been performed using small scale models (Han et al., ; Shu et al., a). However, the similarity parameters have not been fully studied (Anderson and Tsao, ). Thus, the similarity of ice shapes, as well as the thrust and power.Thus, NASA Lewis (LeRC) has begun an effort to develop a database of impact force and energy resulting from shed ice.

This effort consisted of a test of NASA LeRC's Model Rotor Test Rig (MRTR) in the Icing Research Tunnel (IRT). Both natural shedding and forced shedding were investigated.

Forced shedding was achieved by fitting the rotor blades.Summary of NASA Wake and Weather Data Collection at Memphis International Airport: (Invited) NASA PSL LF11 Engine Icing Test Campaign • Wednesday, 15 June • hrs An Assessment of the Icing Blade and the SEA Multi-Element Sensor for Liquid Water Content Calibration of the NASA GRC Icing Research Tunnel.

Laura-Cheri.