국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Axisymmetric Calculations of a Low-Boom Inlet in a Supersonic Wind Tunnel
저자	Chima, Rodrick V.;; Hirt, Stefanie M.;; Reger, Robert
Keyword	COMPUTATIONAL FLUID DYNAMICS;; FLIGHT PATHS;; MACH NUMBER;; MASS FLOW;; STABILITY;; SUPERSONIC AIRCRAFT;; SUPERSONIC INLETS;; WIND TUNNEL WALLS
URL	http://hdl.handle.net/2060/20110023762
보고서번호	NASA/TM-2011-217224
발행년도	2011
출처	NTRS (NASA Technical Report Server)
ABSTRACT	This paper describes axisymmetric CFD predictions made of a supersonic low-boom inlet with a facility diffuser, cold pipe, and mass flow plug within wind tunnel walls, and compares the CFD calculations with the experimental data. The inlet was designed for use on a small supersonic aircraft that would cruise at Mach 1.6, with a Mach number over the wing of 1.7. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center in the fall of 2010 to demonstrate the performance and stability of a practical flight design that included a novel bypass duct. The inlet design is discussed here briefly. Prior to the test, CFD calculations were made to predict the performance of the inlet and its associated wind tunnel hardware, and to estimate flow areas needed to throttle the inlet. The calculations were done with the Wind-US CFD code and are described in detail. After the test, comparisons were made between computed and measured shock patterns, total pressure recoveries, and centerline pressures. The results showed that the dual-stream inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a large stable operating range. Predicted core recovery agreed well with the experiment but predicted bypass recovery and maximum capture ratio were high. Calculations of offdesign performance of the inlet along a flight profile agreed well with measurements and previous calculations.