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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Performance characteristics of frequency translation transponder units for advanced Syncom satellite, and data on multiple access transponder units
Narrative account of Saturn I Launch Vehicle development and mission highlights from 1958 through 1965
Computer program for evaluating space experiments for Saturn in-flight payloads
Performance characteristics of iridium used as high temperature oxidation protective coating for refractory metals
Protective coating effect on stress corrosion properties of supersonic transport skin materials
Stress corrosion cracking of high strength aluminum alloys
Concepts and transformations commonly used in matrix description of polarized waves
Iridium coatings for high temperature oxidation protection on tantalum, niobium, molybdenum, and tungsten
Cryosorption, diffusion pump, and pressure calibration studies in extreme vacuum science and technology application program
Metallurgical effect on superconducting properties of titanium-niobium alloys in solenoid degradation phenomenon study
Safety hazard evaluation for irradiation testing in simulated NERVA environment at cryogenic temperatures
Cross-wire and parallel-gap welding machines evaluation for electronic component bonding
Single-strip cesium-contact ion thrustor for rocket attitude control
Performance specifications and physical parameters of advanced synchronous communications /Syncom/ satellite system and subsystems
Project activities and supporting research for space exploration programs
Effects of porosity level on weld joint performance
Several research areas which have been investigated by the NASA on large scale isolated ducted fan models are discussed. Research concerned with performance has indicated that: (1) ducted fan inlet design does not appear to be a major problem, (2) ducted fan nacelles must be very carefully designed, otherwise the drag becomes excessive, and (3) increasing fan tip clearance reduces the shroud thrust and reduces the capability of the fan for absorbing power. Research concerned with the occurrence of duct lip stall due to angle of attack indicates that neither inner nor outer duct lip stall for reasonably sized ducted fans is the problem that it was once considered to be.
Turboprop, fan-in-wing, and propulsive wing concepts for V/STOL commercical transport aircraft