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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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At least 127 records · Page 7

All sources NASA NTRS DOE OSTI

DOE OSTI2025

ADVANCED RADIOLOGICAL MATERIAL STAGING: THE ENHANCED STAGING PROGRAM AT NNSS

The poster that will be presented at the PATRAM conference that is based on the previously submitted DOE/NV/03624--2192.

42 ENGINEERING↗

NASA NTRS1967

Nose selection and vehicle motion dynamics for the second stage of a two-stage sounding rocket system

Nose selection and vehicle motion dynamics for Nike-Tomahawk rocket

NIKE-TOMAHAWK ROCKET↗

NASA NTRS1968

J-2 engine AS-502 /Apollo 6/ flight report S-2 and S-4B stages. Volume 2 - S-2 stage failure analysis

Postflight analysis of J-2 engine premature shutdown due to fuel system failure resulting in engine damage

Source record↗

NASA NTRS1970

Single stage experimental evaluation of compressor blading with slots and vortex generators. Part 2 - Data and performance for stage 5 without slots or vortex generators

Comparison performance data of compressor blading without slots or vortex generators

Brent, J. A.↗

NASA NTRS1970

Single stage experimental evaluation of compressor blading with slots and vortex generators. Part 1 - Analysis and design of stages 4 and 5

Analysis and design of compressor blading with slots and vortex generators

Brent, J. A.↗

NASA NTRS1976

Design of a 4 1/2 stage turbine with a stage loading factor of 4.66 and high specific work output

The aerodynamic design of a highly loaded multistage fan drive turbine is discussed. Turbine flowpath and airfoil sections are presented along with respective pressure and velocity distributions. Vibrational modes are identified in the expected turbine operating range.

Webster, P. F.↗

NASA NTRS1984

Fuel rich catalytic comustion: The first stage of a two-stage combustor

An experimental program demonstrated that fuel-rich catalytic combustion can be accomplished soot free as long as the combustion temperature is less than the temperature at the rich limit of combustion. Although soot was not measured directly, three pieces of data strongly suggest that it was not present: (1) the product gases were completely transparent and produced no radiation characteristic of soot, (2) measured reaction temperatures followed closely those calculated for equilibrium with no soot present, and (3) over 99 percent of the carbon was accounted for in the measured reaction products. Data for two catalyst configurations were taken along with gas samples at two locations downstream of the catalyst bed.

Brabbs, T. A.↗

NASA NTRS1992