국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure
저자	Robert S. Jankovsky, John M. Kazaroff, and Albert J. Pavli
Keyword	High area ratio; Nozzle; Performance
URL	http://gltrs.grc.nasa.gov/reports/1996/TP-3576.pdf
보고서번호	NASA TP-3576
발행년도	1996
출처	NASA Glenn Research Center
ABSTRACT	An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at com-bustion chamber pressures of 12.4 to 16.5쟋Pa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse.