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Abhijit S. Choudhari
Oklahoma State University, Stillwater, OK 74078, USA

Khaled A. Sallam
School of Mechanical and Aerospace Engineering, Oklahoma State University, Tulsa, OK 74106, USA

DOI: 10.1615/TFEC2017.tpd.017916
pages 3025-3037


A computational study of the exit flow for under expanded supersonic nozzle is conducted using ANSYSFluent R16.2. The study is motivated by the application of supersonic nozzles in air-breathing propulsion systems, e.g. scramjet engines, ramjet engines and afterburners. The simulation of aerated water injected through an aerated liquid injector into a rectangular chamber was conducted using VOF model and SST k-ω turbulence model. The test conditions included: jet exit of 1 mm and mass flow rate of 1.8 kg/s. The results show that air reaches sonic condition at the injector exit due to the Fanno flow effect in the injector passage. The aerated liquid jet exit from the injector is alternately expanded by Prandtl-Meyer expansion fan and compressed by oblique shock waves due to the difference between the back (chamber) pressure and the flow pressure. The process then repeats itself and shock (Mach) diamonds are formed at downstream of injector exit similar to those typical of exhaust plumes of propulsion system. The contours of the Mach number, static pressure are plotted and compared with air injector for under-expanded supersonic nozzles. The agreement of present results with the theory of gas dynamics is excellent.

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