국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Computational Analysis of a Low-Boom Supersonic Inlet
저자	Chima, Rodrick V.
Keyword	ANGLE OF ATTACK;; BYPASSES;; COMPUTATIONAL FLUID DYNAMICS;; DUCTS;; ENGINE INLETS;; INLET AIRFRAME CONFIGURATIONS;; MACH NUMBER;; NOISE REDUCTION;; OVERPRESSURE;; SONIC BOOMS;; SUPERSONIC AIRCRAFT;; SUPERSONIC FLOW;; SUPERSONIC INLETS;; SUPERSONIC WIND TUNNELS;; WIND TUNNEL TESTS
URL	http://hdl.handle.net/2060/20110023757
보고서번호	NASA/TM-2011-217223
발행년도	2011
출처	NTRS (NASA Technical Report Server)
ABSTRACT	A low-boom supersonic inlet was designed for use on a conceptual small supersonic aircraft that would cruise with an over-wing Mach number of 1.7. The inlet was designed to minimize external overpressures, and used a novel bypass duct to divert the highest shock losses around the engine. The Wind-US CFD code was used to predict the effects of capture ratio, struts, bypass design, and angles of attack on inlet performance. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center. Test results showed that the inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a stable operating range much larger than that of an engine. Predictions generally compared very well with the experimental data, and were used to help interpret some of the experimental results.