Aeropropulsion Analysis
Performance of Gas Turbine Engines Using Wave Rotors Modeled
Instrumentation and Control Technology
High-Temperature, Thin-Film Strain Gauges Improved
Silicon Carbide High-Temperature Power Rectifiers Fabricated and Characterized
Automated Hydrogen Gas Leak Detection System
Fuzzy Logic Particle Tracking
Fiber Optic Repair and Maintainability (FORM) Program Progresses
Transient Wave Rotor Performance Investigated
Concept Designed and Developed for Distortion-Tolerant, High-Stability Engine Control
Internal Fluid Mechanics
Coupled Monte Carlo Probability Density Function/SPRAY/CFD Code Developed for
Modeling Gas-Turbine Combustor Flows
CFD-Based Design Optimization Tool Developed for Subsonic Inlet
User Interface Developed for Controls/CFD Interdisciplinary Research
Wavelet Techniques Applied to Modeling Transitional/Turbulent Flows in
Turbomachinery
Effect of Shrouded Stator Leakage Flows on Core Compressor Studied
Stable Lobed Mixer With Combustion Demonstrated and Measured
Effect of Tabs on a Rectangular Nozzle Studied
Propulsion Systems
Spherical Joint Piston and Connecting Rod Developed
Mach 6 Integrated Systems Tests of Lewis' Hypersonic Tunnel Facility
Capabilities Enhanced for Researching the Reduction of Emissions in Future Aircraft
Aircraft Ice Accretion Due to Large-Droplet Icing Clouds
Shape-Memory-Alloy-Based Deicing System Developed
Laser Sheet Flow Visualization Developed for Lewis' Icing Research Tunnel
Gear Crack Propagation Investigation
Study of Gear Dynamic Forces Completed
Code to Optimize Load Sharing of Split-Torque Transmissions Applied to the Comanche
Helicopter
Face Gear Technology for Aerospace Power Transmission Progresses
Advanced Short Takeoff and Vertical Landing (ASTOVL) Concepts Tested
NPARC Code Upgraded With Two-Equation Turbulence Models
Mixing Process in Ejector Nozzles Studied at Lewis' Aero-Acoustic Propulsion Laboratory
F119 Nozzle Flaps Tested at Lewis' CE-22 Facility
Prediction Capability for Transonic Nozzle Afterbodies Improved
Thin-Film Thermocouple Technology Demonstrated for Reliable Heat Transfer
Measurements
Effect of Brush Seals on Wave Rotor Performance Assessed
Scale-Model, Low-Tip-Speed Turbofan Tested at Simulated Takeoff and Approach
Conditions
First Test of Fan Active Noise Control (ANC) Completed
Subsonic Jet Noise Reduced With Improved Internal Exhaust Gas Mixers
Aeropropulsion Facilities and Experiments
Drive Motor Improved for 8- by 6-Foot Supersonic Wind Tunnel/9- by 15-Foot Low-Speed
Wind Tunnel Complex
Testing Efficiency Improved by Addition of Remote Access Control Room
Interdisciplinary Technology Office
Lewis/ACTS/Boeing Experiment Demonstrates Gigabit Application Using ACTS
Heart Pump Design for Cleveland Clinic Foundation
Coupled Aerodynamic-Thermal-Structural (CATS) Analysis
NASA Lewis IITA Kindergarten to 12th Grade Program
Last updated April 26, 1996
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