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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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The Aqua Mission Director has requested the Aqua Flight Operations Team present the current status of the Aqua Constellation Exit Manaeuver (CEM) and End of Mission Plan (EMOP) to the Earth Science Constellation Mission Operations Working Group (MOWG) meeting planned as a virtual meeting from September 29 - October 2, 2020.
Exit boundary layer characteristics were measured for three rectangular nozzles to aid numerical simulations. These results are summarized in this presentation.
Pressure fluctuation spectral peaks due to ‘guided’ (or ‘trapped’) waves in compressible jets in regions upstream of the nozzle exit are investigated experimentally. These spectral peaks are known to disappear in the far acoustic field on the sideline and in the downstream direction, where noise measurements are done typically. The data in this paper show that they are prevalent in the far upstream regions of the ‘forward arc’, at shallow angles relative to the jet axis. This is noted with a round as well as a rectangular jet. The result is significant since such spectral behavior is not predicted by existing noise prediction codes. The experimental results not only expand our understanding of the trapped wave phenomenon but may also aid in refining noise prediction codes for basic as well as application-oriented propulsion systems.
Experimental cross sections are reported for electron excitation of the allowed 2s (sup 2)S 2p - (sup 2)P transition in C(sup 3+).
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Surface chemistry of uranium from gases in the ambient atmosphere of the application environment presents significant challenges due to the high degree of reactivity of the substrate and the ubiquity of these gases in experimental setups. Relatively little is known about the chemical mechanism and reaction rates for the catalytic dissociation of atmospheric gases on solid plutonium or uranium as well as the degradation process to form the metal hydride. Experimental studies and age-aware modeling efforts would greatly benefit from detailed atomistic knowledge of the chemical reactivity in these materials.
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Dynamic loads analysis of space vehicle systems - analytical techniques, ground wind induced loads, engine start and shutdown and launch, atmospheric disturbance, and frequency response
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Measuring distortion characteristics at engine face station of axisymmetric inlet
Auxiliary inlet ejector nozzle designed for supersonic cruise aircraft
Sampling point decrease effects on computed annular combustor parameters and exhaust nozzle temperature profile analysis of thermocouple location
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As design flight speeds are pushed progressively higher, the supersonic inlet becomes an increasingly important component of air-breathing propulsion systems. Currently, the turbojet engine is being considered for application at Mach numbers up to approximately 4 and the ramjet engine for application in the hypersonic region, or Mach numbers of 5 and above. Herein the inlet situation is surveyed and the merits of the various inlet-design philosophies are assessed on the basis of recent experimental data obtained at Mach numbers up to 5.
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