Qualitative investigation of cryogenic fluid injection into a supersonic flow fieldThe behavior of liquid nitrogen injected into a supersonic nitrogen flow field was investigated using an experimental apparatus in which a Mach 2.7 2D gas nitrogen tunnel is coupled with a high-pressure cryogenic source. Observations were monitored and recorded via a video camera and a motion picture camera. It was found that the penetration of a supersonic flow field by injection of liquid nitrogen is strongly dependent on the flow Mach number, the cryogen injection pressure (Pi/Pc), the injector configuration, and the cryogen temperature. For a 2D gaseous N2, Mach 2.7 tunnel, with cryogen injection Pi/Pc approaching 2, the injected fluid penetration for the 1/8-in. injection port approached one half of the tunnel width at 90-deg injection, and one fourth of the tunnel width at 20-deg injection.
Document ID
19920030736
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hendricks, R. C. (NASA Lewis Research Center Cleveland, OH, United States)
Boldman, D. R. (NASA Lewis Research Center Cleveland, OH, United States)
Neumann, H. E. (NASA Lewis Research Center Cleveland, OH, United States)
Vlcek, B. L. (NASA Lewis Research Center Cleveland, OH, United States)