Experimental investigation of a low Reynolds number partial admission single stage supersonic turbine
Partial admission performance of single stage supersonic turbine at low Reynolds numbers
Goldman, L. J.↗
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Results for “Staging”
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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Space shuttle: Static aerodynamic and control investigation of an expendable second stage with payload alone and with delta wing booster (B-15B-1)
Aerodynamic force and moment coefficients for scale model of expendable second stage modified S-2 alone and mounted piggyback on space shuttle booster from Mach 0.6 to 4.96
Allen, E. C.↗
Scheduling technique improvement study for advanced programs. Volume 2: Stage 2 advanced space transport program
Scheduling techniques for manned, reusable orbiting transport vehicle stage of advanced space program
Crain, D. P.↗
Simulation of Saturn V S-II stage propellant feedline dynamics
Saturn 5 S-2 stage propellant feedlines and V-2 engines simulating structural longitudinal oscillation by analog computer
Buchanan, H. J.↗
Back recovery microstrains in stage II deformation of copper
Nonelastic unloading microstrains in Cu crystals after stage II macroscopic prestraining, discussing stresses action on dislocations
Roberts, J. M.↗
Evidence from hard X-rays for two-stage particle acceleration in a solar flare
Solar flare two stage particle acceleration from X-ray burst observations, discussing induced electric field and Fermi mechanism
Dennis, B. R.↗
Erosion of a three-stage potassium turbine
Three stage potassium vapor turbine for space systems electric power generation, discussing erosion and endurance tests
Kaplan, G. M.↗
High-performance spray-foam insulation for application on Saturn S-II stage
Spray foam insulation for Saturn S-2 stage, consisting of phenolic honeycomb core composite purged with helium
Mack, F. E.↗
Two-stage coaxial gas compressor
Compressor raises pressure of gases from low ambient supply during space experiments by a system of low weight, size, and power input. Dc rotary-torque motor and ball-screw drive shaft activate first and second stage of compressor, utilizing inertia forces to operate check valves.
Wang, W. S.↗
Space shuttle: Static stability and control investigation of the NR-GD/C delta wing booster (B-15B-1) and a Reusable Nuclear Stage (RNS) M = 0.6 - 4.96
Experimental aerodynamic investigations were made in the NASA/MSFC 14 x 14 inch trisonic wind tunnel on a NR-GD/C 0.0031 scale model delta wing booster (B-15B-1) and reusable nuclear stage (RNS). Three basic configurations were tested: (1) the B-15B-1 booster alone, (2) the RNS alone, and (3) the booster with the RNS mounted piggyback. Six component force and moment data were recorded for each of these configurations over an angle of attack range from -16 deg to 4 deg at zero degrees sideslip, and over an angle of sideslip range from -10 deg to 10 deg at zero and -6 degrees angle of attack. The configurations were tested over a Mach number range of 0.6 to 5.0 with a nominal Reynolds number of 6.5 million per foot except for Mach 1.2 and 3.0 where the Reynolds number were 12.4 million and 4.4 million per foot respectively.
Allen, E. C.↗
Space shuttle staging simulation
The overall capability is described and delineated of a new digital computer program for simulation of space shuttle vehicle staging maneuvers. The important distinctive feature of the program is that it enables simulation of linkage-type separation devices (as well as all the more usual types) and includes the effects of interference aerodynamics and thrust impingement. A general flow description and a moderately detailed description of the major simulation components are presented. Some typical simulation results are shown, and the flexibility and growth potential of the basic simulation are discussed.
Hall, C. E.↗
Effect of grooved casing treatment on the flow range capability of a single-stage axial-flow compressor
Comparisons of the results of testing a single-stage axial-flow compressor with a solid-wall casing and with grooved casings are presented. The depth, location, and number of circumferential grooves in the casing over the casing over the rotor tip were varied. The near-stall weight flow was lower than that with the solid-wall casing for all but one grooved configuration indicating an improvement in the stall margin. The greatest reduction in the near-stall weight flow was noted for the configuration with five grooves located over the blade midchord region.
Bailey, E. E.↗
Sleep-wake cycle effects on sleep stages, and plasma cortisol and growth secretions
Studies were made of the effects of various stimuli on sleep stages and of secretion of a number of different hormones during sleep in human subjects. Among the stimuli were vestibular stimulation, the action of L-Dopa, and a three-hour sleep-wake cycle. Hormones observed included plasma cortisol, growth hormone, dehydroisoandrosterone, and luteinizing hormone. Relationships between sleep onset, the presence of Cushing's syndrome or sleep disorders, and ultradian rhythmicity, and hormone secretion were investigated. Sleep patterns and hormone secretion in normal subjects were also studied.
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The developing stages of the Martian yellow storm of 1971
A history of the yellow storm on Mars which occurred in 1971 is presented. It is compared to the Great 1956 Yellow Cloud, and possible yellow storms are predicted for 1973. Photographs of the stages of evolution and the path of the storm are included.
Capen, C. F.↗
Effect of Reynolds number on overall performance of a 3.7-inch-diameter six-stage axial-flow compressor
A 9.4-centimeter (3.7-in.) diameter six-stage axial-flow compressor was tested in argon over a range of inlet pressures corresponding to a Reynolds number range of 30,600 to 160,000. The effect of Reynolds number on efficiency, pressure ratio, work input, maximum flow, and surge is shown. The Reynolds number effects are discussed in terms of changes in boundary-layer thickness, losses, and the resulting changes in throughflow velocity. Significant deviation was noted from the 0.2 power relation often used to express the variation of loss with Reynolds number.
Heidelberg, L. J.↗
Improved scaling laws for stage inert mass of space propulsion systems. Volume 1: Summary
Summarized is a study which satisfies the need for improved scaling laws for stage inert mass of space propulsion systems. The resulting laws are applicable to current and future vehicle systems and designs for a comprehensive spectrum of anticipated planetary missions.
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Improved scaling laws for stage inert mass of space propulsion systems. Volume 2: System modeling and weight data
Technical models and analytical approaches used to develop the weight data for vehicle system concepts using advanced technology are reported. Weight data are supplied for the following major system elements: engine, pressurization, propellant containers, structural shells and secondary structure, and environmental protection shields for the meteoroid and thermal design requirements. Scaling laws, improved and a simplified set, are developed from the system weight data. The laws consider the implications of the major design parameters and mission requirements on the stage inert mass.
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Improved scaling laws for stage inert mass space Propulsion systems. Volume 3: Propulsion synthesis program users and programmers manual
The analytical models developed for the Space Propulsion Automated Synthesis Modeling (SPASM) program are presented. Weight scaling laws developed during this study are incorporated into the program's scaling data bank. A detail listing, logic diagram and input/output formats are supplied for the SPASM program. Two test examples for one to four-stage vehicles performing different types of missions are shown to demonstrate the program's capability and versatility.
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