Mechanisms of Rotating Instability in Axial Compressors Investigated
Two-Stage Axial Compressor Rig Designed To Develop and Validate Advanced Aerodynamic Technologies
Centrifugal Compressor Surge Controlled
Significance of Compressor Blade Row Interactions on Loss Production Investigated
Glenn-HT Code Validated for Complex Turbine Blade Cooling Passage
National Combustion Code Validated Against Lean Direct Injection Flow Field Data
High-Pressure Gaseous Burner (HPGB) Facility Became Operational
Spontaneous Raman Scattering (SRS) System for Calibrating High-Pressure Flames Became Operational
Nanotechnology Investigated for Future Gelled and Metallized Gelled Fuels
Solid Hydrogen Particles and Flow Rates Analyzed for Atomic Fuels
Low NOx, Lean Direct Wall injection Combustor Concept Developed
Large-Eddy Simulation Code Developed for Propulsion Applications
Sound Sources Identified in High-Speed Jets by Correlating Flow Density Fluctuations With Far-Field Noise
Air-Breathing Launch Vehicle Technology Being Developed
Last updated: June 25, 2003
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