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  • 1
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    Transverse injection of a particle-laden liquid jet in supersonic flow: A three-phase flow (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-12-21
    Description: The results of a two part study of the behavior of particle laden liquid jets injected into air are presented. Water was used as the liquid carrier and either 1-37 or 13-44 microns diam. spherical glass beads with a specific gravity of 2.8-3.0 as the particles. The observations were mainly photographic. The breakup of jets injected into still air was investigated as a function of particle loading, and the results were compared to the pure liquid jet case. The jets were found to be more stable with particles present. The length to breakup was increased, and the formation of satellite droplets was suppressed. The penetration and breakup of transverse jets in a Mach 3.0 air stream was studied. The general breakup mechanism of wave formation was found to be the same as for the all liquid case. Significant separation of the phases was observed, and the penetration of the liquid phase was reduced compared to all liquid cases at the same value of the jet to free stream momentum flux ratio.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA. Langley Research Center The 17th JANNAF Combust. Meeting, Vol. 1; p 587-604
    Format: text
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  • 2
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    Turbulent mixing /analysis/ (1967)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Approximate methods for solving differential equations of motion to predict free turbulent mixing processes - single-form eddy viscosity model
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 3
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    Two-dimensional mixing studies (1967)
    In:  CASI
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    Publication Date: 2006-10-26
    Description: Two-dimensional turbulent mixing scaling laws of mixing, heat transfer and skin friction for use in design of scramjet engine combustors
    Keywords: PROPULSION SYSTEMS
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  • 4
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    Mixing studies of helium in air at high supersonic speeds (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 9, Se; 2234-224
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  • 5
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    Skin friction measurements in high temperature high speed flows (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An experimental investigation was conducted to measure skin friction along the chamber walls of supersonic combustors. A direct force measurement device was used to simultaneously measure an axial and transverse component of the small tangential shear force passing over a non-intrusive floating element. The floating head is mounted to a stiff cantilever beam arrangement with deflection due to the flow on the order of 0.00254 mm (0.0001 in.). This allowed the instrument to be a non-nulling type. A second gauge was designed with active cooling of the floating sensor head to eliminate non-uniform temperature effects between the sensor head and the surrounding wall. Samples of measurements made in combustor test facilities at NASA Langley Research Center and at the General Applied Science Laboratory (GASL) are presented. Skin friction coefficients between 0.001 - 0.005 were measured dependent on the facility and measurement location. Analysis of the measurement uncertainties indicate an accuracy to within +/- 10-15 percent of the streamwise component.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Langley Research Center, The 1992 NASA Langley Measurement Technology Conference: Measurement Technology for Aerospace Applications in High-Temperature Environments; p 171-188
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  • 6
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    Surface pressures on a flat plate with dual jet configurations (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2456, Accession no. A83-38677
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 484-490
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  • 7
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    Rectangular jets in a crossflow (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Rectangular jets injected from a flat plate into a crossflow at large angles have been studied. Results were obtained as surface pressure distributions, mean velocity vector plots, turbulence intensities, and Reynolds stresses in the jet plume. The length-to-width ratio of the jets was 4, and the jets were aligned streamwise as single and side-by-side dual jets. The jet injection angles were 90 and 60 deg. Surface pressure distribution results were obtained for jet-to-freestream velocity ratios of 2.2, 4, and 8. Mean flow and turbulence flowfield data were obtained for the side-by-side dual jets, mainly for the jet-to-freestream velocity ratio of 4. The jets featured strong negative pressure peaks near the front nozzle corners. The 60-deg jets produced lower magnitude negative pressures, which are distributed over a lesser area when compared to the 90-deg jets.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 793-804
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  • 8
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    Effects of swirl and high turbulence on a jet in a crossflow (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An experimental study has been conducted on the effects of initial swirl and high turbulence in the exhaust of a circular jet injected from a flat plate at a 90-deg angle into a crossflow. The different jet types studied were low-exit turbulence (3 percent), high-exit turbulence (over 10 percent), and 40 and 58 percent swirl. Surface pressure distributions and mean velocity vector plots were obtained for all of these cases. For the surface pressure distribution tests, the jet to crossflow velocity ratios R were 2.2, 4, and 8 for most of the jet types. For the mean velocity vector plots, R = 4 was chosen. Turbulence information in the jet plume was also obtained for the low-exit turbulence case at R = 4. The results showed that the higher-exit turbulence reduced the penetration height, and it also reduced the surface area influenced by negative pressures. The swirl-caused asymmetric pressure distributions and the swirl effects were more pronounced for lower-velocity ratios.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 539-546
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  • 9
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    Free turbulent mixing in a coflowing stream (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The major points are described of a turbulent transport model of the classical, gradient transport, eddy viscosity type. The relationship is discussed of the developed model to the Prandtl (jet mixing) model, the Schlichting (wake) model, and the Clauser (boundary layer) model. Limitations of the model and test cases are summarized.
    Keywords: FLUID MECHANICS
    Type: NASA. Langley Res. Center Free Turbulent Shear Flows, Vol. 1; p 259-275
    Format: application/pdf
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  • 10
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    Mixing studies of helium in air at Mach 6 (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Concentration and mean flow measurements with nanoshadowgraphs and surface flow visualization have been obtained by a study of mixing phenomena during gas injection into hypersonic flow. At Mach 6, a comparison of the matched-pressure injection case with the underexpanded case indicated a greater injectant core penetration rate and a greater concentration-decay rate, leading to a shorter distance for the injectant core to reach an H2-air stoichiometric ratio. The entire injectant plume remained supersonic, and only moderate pressure losses were found. While injector yaw did not increase the mixing rates, it led to an increase in overall injectant plume cross-section, with consequent increase in the size of the mixing region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-2268
    Format: text
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