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  • Aircraft Design, Testing and Performance  (1)
  • Aircraft Propulsion and Power; Air Transportation and Safety  (1)
  • INSTRUMENTATION AND PHOTOGRAPHY  (1)
  • 1
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    Pressure-Sensitive Paint Applied to Ice Accretions (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Aircraft icing occurs when a plane flies through a cloud of supercooled water droplets. When the droplets impinge on aircraft components, ice starts to form and accumulate. This accumulation of ice severely increases the drag and lift of the aircraft, and can ultimately lead to catastrophic failures and even loss of life. Knowledge of the air pressures on the surfaces of ice and models in wind tunnels allows researchers to better predict the effects that different icing conditions will have on the performance of real aircraft. The use of pressure-sensitive paint (PSP) has provided valuable information on similar problems in conventional wind tunnel testing. In NASA Lewis Research Center Icing Research Tunnel, Lewis researchers recently demonstrated the world s first application of PSP on actual ice formed on a wind tunnel model. This proof-of-concept test showed that a new paint formulation developed under a grant by the University of Washington adheres to both the ice shapes and cold aluminum models, provides a uniform coating that preserves the detailed ice shape structure, and responds to simulated pressure changes.
    Keywords: Aircraft Design, Testing and Performance
    Type: Research and Technology 1998; NASA/TM-1999-208815
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Improved Speed Control System for the 87,000 HP Wind Tunnel Drive (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the design, installation, and integrated systems tests for a new drive motor speed control system which was part of a recent rehab project for the NASA Lewis 8x6 Supersonic Wind Tunnel. The tunnel drive consists of three mechanically-coupled 29,000 HP wound rotor induction motors driving an axial flow compressor. Liquid rheostats are used to vary the impedance of the rotor circuits, thus varying the speed of the drive system. The new design utilizes a distributed digital control system with a dual touch screen CRT operator console to provide alarm monitoring, logging, and trending. The liquid rheostats are driven by brushtype servomotor systems with magnetostrictive linear displacement transducers used for position feedback. The new system achieved all goals for speed variations with load, motor load balance, and control of total power.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-106840 , E-9404 , NAS 1.15:106840 , International Instrumentation Symposium; May 07, 1995 - May 11, 1995; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An Initial Study of the Fundamentals of Ice Crystal Icing Physics in the NASA Propulsion Systems Laboratory (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents results from an initial study of the fundamental physics of ice-crystal ice accretion using the NASA Propulsion Systems Lab (PSL). Ice accretion due to the ingestion of ice-crystals is being attributed to numerous jet-engine power-loss events. The NASA PSL is an altitude jet-engine test facility which has recently added a capability to inject ice particles into the flow. NASA is evaluating whether this facility, in addition to full-engine and motor-driven-rig tests, can be used for more fundamental ice-accretion studies that simulate the different mixed-phase icing conditions along the core flow passage of a turbo-fan engine compressor. The data from such fundamental accretion tests will be used to help develop and validate models of the accretion process. The present study utilized a NACA0012 airfoil. The mixed-phase conditions were generated by partially freezing the liquid-water droplets ejected from the spray bars. This paper presents data regarding (1) the freeze out characteristics of the cloud, (2) changes in aerothermal conditions due to the presence of the cloud, and (3) the ice accretion characteristics observed on the airfoil model. The primary variable in this test was the PSL plenum humidity which was systematically varied for two duct-exit-plane velocities (85 and 135 ms) as well as two particle size clouds (15 and 50 m MVDi). The observed clouds ranged from fully glaciated to fully liquid, where the liquid clouds were at least partially supercooled. The air total temperature decreased at the test section when the cloud was activated due to evaporation. The ice accretions observed ranged from sharp arrow-like accretions, characteristic of ice-crystal erosion, to cases with double-horn shapes, characteristic of supercooled water accretions.
    Keywords: Aircraft Propulsion and Power; Air Transportation and Safety
    Type: GRC-E-DAA-TN42447 , AIAA Aviation 2017 Conference; Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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