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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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Wind tunnel tests to determine effect of angle of attack on maximum lift at stall for half-wing models, and single engine, jet propelled aircraft
Maximum magnetic moment of Venus from magnetic field and solar wind measurements obtained by Mariner II
Radiation belt boundary determined by trapping boundary for energetic electrons during solar cycle maximum period
In-tank shutoff valve is installed with the valve poppet and actuator inside the tank to provide maximum blast protection during rocket engine test operation. This valve design is applicable wherever explosive fuels are used and is currently being used in lox and liquid hydrogen tanks at a rocket engine test site.
Maximum lift-drag ratios for slender flat-top homothetic bodies flying at hypersonic speeds
Satellite electric power system configurations for maximum utilization of power - systems analysis
Maximum probability estimators and conservative confidence interval models for reliability growth problems with debugging phase
Determination of maximum Chlorella photosynthesis
One-dimensional approach to maximum lift-drag ratio of slender, flat-top, affine wing at hypersonic speeds
Two-dimensional approach to maximum lift-drag ratio of slender, flat-top, wing at hypersonic speeds
Satellite power system configurations for maximum utilization of power
Micrometeoroid cratering effects on axis direction of maximum moment of inertia
Electronic instrument system for determining temperature effects on maximum induction of magnetic materials
Positive ion temperatures above F layer maximum from Ariel I satellite ion mass analyzer
Ionic composition above F layer maximum from Ariel I satellite ion mass spectrometer
Maximum lift-to-drag ratios of two-dimensional, slender, power-law wings in hypersonic flow
Analysis of satellite electric power systems configurations for maximum power use
Analytical solution to determine rocket design for maximum payload energy