Estimating and explaining the spread of COVID-19 at the county level in the USA
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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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Measurements of shock wave overpressures from airplanes at altitudes to 75,000 feet & supersonic speed
Surface modifications of recovered small-scale plastic models after high speed flight used to estimate extent of laminar and turbulent flow over surface related to ablation studies
Desensitizing microcircuits to variations in temperature and performance parameters - computer aided sensitivity analysis
Mathematical analysis of flame propagation at high pressures over surface of igniting solid propellants and propellant ingredients in oxygen/inert atmospheres
Space technological capabilities and developments in US, USSR, Western Europe, Japan, China, and developing nations
Doppler frequency shift correction device for multiplex communication with Applications Technology Satellites
Schlieren photography of flow distribution for transverse hydrogen jets from flat plate into Mach 2.72 airstream
It is suggested that convective electric fields in the equatorial ionosphere are generated by neutral winds (zonal or meridional) which act on regions having structure in their field aligned Pedersen conductivity integrals. The conductivity structure is presumably caused by long-lived metallic ions concentrated irregularly below the F layer at altitudes where their collision and gyrofrequencies are comparable. The resulting plasma convection leads to large-scale irregularities and sets up gradients in the electric field that drive other instability mechanisms to produce small-scale irregularities. The mechanism proposed requires a different velocity above and below 200 km for winds in the magnetic east-west direction, but for winds in the magnetic meridian direction, an altitude gradient is not required.
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The drag of a simulated scramjet combustion module was measured at Mach 2, 2.5, and 3. The combustor was rectangular in cross section and incorporated six swept fuel injector struts. The effect of strut leading edge radius, position of maximum thickness, thickness ratio, sweep angle, and strut length on the drag was determined. Reduction in thickness ratio had the largest effect on drag reduction. Sweeping the struts upstream yielded the same drag as sweeping the struts downstream and potentially offers the advantages of increased mixing time for the fuel. Helium injection was used to simulate hydrogen fuel. The interstrut spacing required to achieve good distribution of fuel was was found to be about 10 jet diameters. The contribution of helium injection to drag reduction was small.
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