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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 253 records · Page 14
All sourcesNASA NTRSDOE OSTI
NASA NTRS1964

Comments on exhaust flow field and surface impingement

In recent months there has been interest in the problem of the impingement of a jet exhaust on simulated lunar surfaces. The problem has been described both experimentally and theoretically. In the June issue of the AIAA Journal there appeared two Technical Notes that seemed to complicate unnecessarily the analysis of the free-jet expansion and the surface pressure distribution. The purpose of the present comment is to recall briefly the simple results of the theory and to make a more complete comparison with the experiniental data of Ref. 1

LUNAR SURFACE↗
NASA NTRS1965

Experimental investigation of jet impingement on surfaces of fine particles in a vacuum environment

The erosion characteristics of a bed of fine particles under vacuum conditions (10 -4 torr) resulting from an impinging jet exhaust were investigated for various particle sizes and jet heights above the dust surface. The investigation included measurements of the craters during erosion, measurements of the visibility reduction, and photographs of the erosion process. The results of this investigation indicate that there exists a finite jet height above which particles will not be eroded. This height, for given nozzle conditions, varies with surface-particle size. In addition, the results indicate that the magnitude of surface erosion also depends on-surface-particle size; erosion is most rapid with the coarsest particles. These and other associated test results are presented and compared with available theory.

Jet exhaust↗
NASA NTRS1968

Two-fluid, impinging-sheet injector

Two-fluid, impinging-sheet propellant injector reduces the severe erosion found to occur when ejector elements are directly exposed during throttling without the benefits of a cooling flow of the propellant liquids. It greatly improves combustion efficiency by venting the secondary stream of combustion gases generated by backspray reaction.

Riebling, R. W.↗