Heat transfer in 30 deg and 60 deg half-angle of convergence nozzles with various diameter uncooled pipe inlets
Heat transfer in convergent nozzles with various uncooled pipe inlets
HEAT TRANSFER↗
SEARCH · Search NASA
Results for “diameter”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
An investigation of solar emission at frequencies of 35, 70, and 94 Gc with a 4.88- meter diameter telescope.
Solar radio emission spectroheliograms at different millimeter wave frequencies
MILLIMETER WAVE↗
Experimental investigation of a 1.5-meter diameter Kaufman thrustor.
Kaufman thrustor with curved stainless steel accelerating-grid system, studying operation, efficiency, plasma instability, etc
THRUSTOR↗
Electric arc-driven shock tube diameter, length and energy requirements for the study of gas radiation phenomena
Explore the source record for details and available documents.
Livingston, F. R.↗
Flight test of a 40-foot-nominal-diameter modified ringsail parachute deployed at a Mach number of 1.64 and a dynamic pressure of 9.1 pounds per square foot
Flight tests of ringsail parachute with 15 percent porosity, for planetary entry
Eckstrom, C. V.↗
Flight test of a 15-foot-diameter /4.6-meter/ 120 deg conical spacecraft simulating parachute deployment in a Mars atmosphere
Flight test of conical spacecraft simulating parachute deployment in Mars atmosphere
Darnell, W. L.↗
Performance of a 19.7 meter diameter disk gap band parachute in a simulated Martian environment
Inflation, and drag characteristics of disk gap band parachute in simulated low density Mars atmosphere
Bendura, R. J.↗
Performance of a 16.6-meter-diameter modified ringsail parachute in a simulated Martian environment
Inflation, drag, and stability characteristics of ringsail parachute deployed in simulated Mars atmosphere
Coltrane, L. C.↗
Performance in air of 4 inch /10.16-cm/ mean-diameter single stage axial-flow turbine for Reynolds numbers from 4,900 to 188,000
Reynolds number effect on single stage axial flow turbine in air
Klassen, H. A.↗
Experimental performance evaluation of an 8.5 inch /21.59 cm/ mean-diameter axial flow turbine at Reynolds numbers from 18,000 to 177,000
Effects of Reynolds number change on performance of axial flow turbine working in argon
Kofskey, M. G.↗
Design, manufacture and application of prefabricated vacuum super insulation panels to a 70-inch diameter cryogenic test tank Final report
Design, manufacture, and application of prefabricated, vacuum-evacuated, insulation panels to 70-inch diam cryogenic test tank
Lindquist, C. R.↗
Fifty-five foot diameter ringsail parachute. Planetary entry parachute program Final technical report
Material strengths, shock loading, and material stress analyses for planetary entry ringsail parachute design
Stone, F. J.↗
Forty ft-diameter ringsail parachute planetary entry parachute program Final technical report
Design calculations and materials test data for planetary entry ringsail parachute
Stone, F. J.↗
Sixty-five foot diameter DGB parachute planetary entry parachute program Design report
Structural design and component test data for disk gap-band planetary entry parachute
Lemke, R. A.↗
Performance of a 16.6-meter-diameter cross parachute in a simulated Martian environment
Inflation and drag characteristics of cross parachute in simulated Martian environment
Coltrane, L. C.↗
Experimental evaluation of 7.82-inch /19.8-cm/ diameter throat inserts in a storable-propellant rocket engine
Failure mechanisms for specific materials and design concepts for storable propellant rocket engines
Peterson, D. A.↗
Dynamic stability of a 4.6-meter-diameter 120 deg conical spacecraft at Mach numbers from 0.78 to 0.48 in a simulated Martian environment
Subsonic dynamic stability characteristics of large conical spacecraft in simulated Martian environment
Bendura, R. J.↗
Cavitating performance of two low-area-ratio water jet pumps having throat lengths of 7.25 diameters
Cavitation performance of jet pumps having low ratios of nozzle to throat area
Sanger, N. L.↗