NDLI: Progress toward synergistic hypermixing nozzles

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Progress toward synergistic hypermixing nozzles

Content Provider	NASA Technical Reports Server (NTRS)
Author	Davis, D. O. Hingst, W. R.
Copyright Year	1991
Description	Mean flow measurements were obtained for air-to-air mixing downstream of swept and unswept ramp wall mounted hypermixing nozzle configurations. Aside from the sweep of the ramps, the two nozzle configurations studied are identical. The nozzles inject three parallel supersonic jets at a 15 deg angle (relative to the wind tunnel wall) into a supersonic freestream. Mach number and volume fraction distributions in a transverse plane 11.1 nozzle heights downstream from the nozzle exit plane were measured. Data are presented for a freestream Mach number of three at a matched static pressure condition and also at underexpanded static pressure condition (pressure ratio = 5). Surface oil flow visualization was used to study the near wall flow behavior. The results indicate that the swept ramp injectors produce stronger and larger vortex pairs than the unswept ramp injectors. The increased interaction between the swept ramp model's larger vortex pairs yields better mixing characteristics for this model.
File Size	9945275
Page Count	14
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910019836
Archival Resource Key	ark:/13960/t94799g29
Language	English
Publisher Date	1991-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Static Pressure Injectors Flow Measurement Wind Tunnel Walls Nozzle Geometry Air Flow Concentration Composition Jet Mixing Flow Nozzle Design Vortices Wall Flow Supersonic Jet Flow Flow Visualization Pressure Ratio Free Flow Fuel-air Ratio Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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