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기술보고서

기술보고서 게시판 내용
타이틀	Results of an Advanced Fan Stage Operating Over a Wide Range of Speed and Bypass Ratio : Part 2;; Comparison of CFD and Experimental Results
저자	Celestina, Mark L.;; Suder, Kenneth L.;; Kulkarni, Sameer
Keyword	AERODYNAMIC STALLING;; BOUNDARY CONDITIONS;; BYPASS RATIO;; COMPUTATIONAL FLUID DYNAMICS;; COMPUTERIZED SIMULATION;; FLIGHT CONDITIONS;; INLET FLOW;; LESSONS LEARNED;; MASS FLOW;; PRESSURE RATIO;; SEA LEVEL;; SUPERSONIC SPEED;; TRANSONIC COMPRESSORS;; TURBOFANS
URL	http://hdl.handle.net/2060/20100040416
보고서번호	NASA/TM-2010-216769/PART2
발행년도	2010
출처	NTRS (NASA Technical Report Server)
ABSTRACT	NASA and GE teamed to design and build a 57 percent engine scaled fan stage for a Mach 4 variable cycle turbofan/ramjet engine for access to space with multipoint operations. This fan stage was tested in NASA''s transonic compressor facility. The objectives of this test were to assess the aerodynamic and aero mechanic performance and operability characteristics of the fan stage over the entire range of engine operation including: 1) sea level static take-off;; 2) transition over large swings in fan bypass ratio;; 3) transition from turbofan to ramjet;; and 4) fan wind-milling operation at high Mach flight conditions. This paper will focus on an assessment of APNASA, a multistage turbomachinery analysis code developed by NASA, to predict the fan stage performance and operability over a wide range of speeds ࿅ to 100 percent) and bypass ratios.