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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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Two-dimensional purely elastic Earth model used to study elastic equilibrium configuration between density and topographic surface irregularities
Computer program provides elastic analysis of highly redundant structural configurations. Punched output of flexibility and stiffness matrices are obtained for use in a natural frequency analysis. Member reaction output in card or tape form is used in conjunction with other programs to perform stress analyses.
Subsonic longitudinal aerodynamic characteristics of semiapex angle conical reentry configuration
Effects of injector face baffle configurations on screech in hydrogen-oxygen rocket engine
Aerodynamic characteristics of blunt, lifting body reentry configuration
Multicable configuration analyses and computer programs on aerodynamic characteristics and stability of captive balloons for airborne instrumentation
Aerodynamic characteristics of wing body configurations with canard controls determined in hypersonic flow apparatus
Apollo wind tunnel test program and configuration design developments
Interplanetary spacecraft power supply system configurations and solar cell array analysis
Liquid equilibrium configurations and disturbances of vehicle motion due to liquid sloshing in space
Flow field, pressure distributions, and heat transfer distribution of several tension shell configurations at hypersonic speeds
Optimum power system configurations for planetary spacecraft probes
Configuration interaction in helium continuum and autoionization levels
Low subsonic static and dynamic stability characteristics of blunt 120 deg conical configuration
Thermocouple wire size and configuration effects on internal temperature measurements in charring ablator
Skewed wing tip control effects on variable sweep wing-fuselage configuration
Analysis and configuration of control system for Mars propulsive lander
Aerodynamic characteristics for cone-cylinder and cone cylinder frustrum cylinder configurations - linear aerodynamic load distributions at Mach numbers from 0.7 to 1.96