Status of a five-centimeter-diameter ion thruster technology program
Prototype auxiliary propulsion subsystem with isolated single tank propellant feed system and 5-cm-diameter ion thruster
Banks, B. A.↗
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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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Method and apparatus for precision sizing and joining of large diameter tubes Patent
Method and apparatus for portable high precision magnetomotive bulging, constricting, and joining of large diameter metal tubes
Bennight, J. D.↗
Effective separation technique for small diameter whiskers
Evaluation of technique for separating small diameter whiskers from as-grown matt for use as reinforcing fibers in whisker composites
Westfall, L. J.↗
Method and apparatus for precision sizing and joining of large diameter tubes Patent
Method and apparatus for precision sizing and joining of large diameter tubes by bulging or constricting overlapping ends
Bennight, J. D.↗
Development and testing of ablative rocket engine with selected 7.62-centimeter /3.0 in/ diameter throat inserts
Development and testing of ablative rocket engine with selected 7.62 cm /3.0 in./ diameter throat inserts, and testing of zirconia reinforced with tungsten-rhenium wire for throat insert material
Pavli, A. J.↗
Development of large diameter T-111 /Ta-8W-2Hf/ tubing Final report
Large diameter T-111 tubing processed from seamless and welded tube shells
Buckman, R. W., Jr.↗
High-Altitude Flight Test of a Reefed 12.2-Meter-Diameter Disk-Gap-Band Parachute with Deployment at a Mach Number of 2.58
High altitude flight test of reefed 12.2-meter-diameter disk-gap-band parachute with deployment at 2.58 Mach number
Preisser, J. S.↗
Criticality study of NASA solution reactors with 25.4-centimeter diameter cylindrical stainless-steel tanks
Criticality study of ZPR-1 and ZPR-2 with 25.4-cm diameter cylindrical stainless steel cores
Fox, T. A.↗
A 1000-hour test of a dual grid, electrostatic beam deflection accelerator system on a 5-centimeter-diameter Kaufman thruster
Dual grid accelerator system with electrostatic beam deflection capability tested on 5-cm diameter Kaufman thruster for 1000 hours
Lathem, W. C.↗
Effect of neutralizer position on accelerator wear for a 30 centimeter diameter ion bombardment thruster
Neutralizer location for minimum accelerator erosion on 30 centimeter diameter ion bombardment thruster
Bechtel, R. T.↗
Methods and procedures for evaluating, forming, and installing small diameter sheathed thermocouple wire and sheathed thermocouples
Methods and procedures for evaluating, forming, and installing small diameter thermocouple wire and sheathed thermocouples
Crowl, R. J.↗
Determination of origin of small lunar and terrestrial craters by depth diameter ratio
Small lunar and terrestrial craters, determining impact or volcanic origin by depth-diameter ratio
Smith, E. I.↗
Experimental effects of pressure, subcooling, and diameter on thin-wire film boiling of liquid nitrogen
Pressure, subcooling and diameter effects on heat transfer and circumferencial flow transition of thin wire film boiling of liquid nitrogen in pool
Baumeister, K. J.↗
The polarization curve and the absolute diameter of Vesta
Photoelectric polarization curve, reflectivity and absolute diameter of Vesta, comparing with Lyot curve
Veverka, J.↗
A study of performance and cost improvement potential of the 120 inch (3.05 m) diameter solid rocket motor. Volume 1: Summary report
A parametric study of ballistic modifications to the 120 inch diameter solid propellant rocket engine which forms part of the Air Force Titan 3 system is presented. 576 separate designs were defined and 24 were selected for detailed analysis. Detailed design descriptions, ballistic performance, and mass property data were prepared for each design. It was determined that a relatively simple change in design parameters could provide a wide range of solid propellant rocket engine ballistic characteristics for future launch vehicle applications.
Backlund, S. J.↗
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.↗
A 640 foot per second impact test of a two foot diameter model nuclear reactor containment system without fracture
An impact test was conducted on an 1142 pound 2 foot diameter sphere model. The purpose of this test was to determine the feasibility of containing the fission products of a mobile reactor in an impact. The model simulated the reactor core, energy absorbing gamma shielding, neutron shielding and the containment vessel. It was impacted against an 18,000 pound reinforced concrete block. The model was significantly deformed and the concrete block demolished. No leaks were detected nor cracks observed in the model after impact.
Puthoff, R. L.↗
Fan and wing force data from wind tunnel investigation of a 0.38 meter (15 inch) diameter VTOL model lift fan installed in a two dimensional wing
Test data are presented for a 38-cm (15-in.) diameter, 1.28 pressure ratio model VTOL lift fan installed in a two-dimensional wing and tested in a 2.74-by 4.58-meter (9-by 15-ft)V/STOL wind tunnel. Tests were run with and without exit louvers over a wide range of crossflow velocities and wing angle of attack. Tests were also performed with annular-inlet vanes, inlet bell-mouth surface disconuities, and fences to induce fan windmilling. Data are presented on the axial force of the fan assembly and overall wing forces and moments as measured on force balances for various static and crossflow test conditions. Midspan wing surface pressure coefficient data are also given.
Yuska, J. A.↗