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  • 1
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    Incipient cross-stream liquid jet atomization at high altitude and velocity (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Liquid jets aerodynamic atomization at orifice exit in reentry vehicle into gaseous crossflow, investigating critical Weber number variation with Knudsen number
    Keywords: FLUID MECHANICS
    Type: ; ACE(
    Format: text
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  • 2
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    Atomization of superheated water jets at low ambient pressures. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Atomization characteristics of superheated water jets from basic orifices at low Weber numbers
    Keywords: FLUID MECHANICS
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  • 3
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    Measurement of mean drop sizes for sprays from superheated waterjets. (1969)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Mean drop size generated in vapor pressure regime of liquid water jet, noting effect of water temperature and orifice diameter
    Keywords: FLUID MECHANICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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  • 4
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    Experimental investigation of a plasma covered, axially slotted cylinder antenna (1969)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Equatorial patterns measurement of plasma covered axially slotted cylindrical antenna, describing discharge tube, facility and Langmuir probe survey of tube electron density
    Keywords: ELECTRONIC EQUIPMENT
    Type: ; ACE(
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  • 5
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    Flow field studies using holographic interferometry at Langley (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some of the uses of holographic interferometry at Langley Research Center both for flow visualization and for density field determinations are described and tests in cryogenic flows at the Langley 0.3-Meter Transonic Cryogenic Tunnel are discussed. Experimental and theoretical fringe shift data are compared.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Flow Visualization and Laser Velocimetry for Wind Tunnels; p 193-204
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  • 6
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    Exploratory tests of two strut fuel injectors for supersonic combustion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of supersonic mixing and combustion tests performed with two simple strut injector configurations, one with parallel injectors and one with perpendicular injectors, are presented and analyzed. Good agreement is obtained between static pressure measured on the duct wall downstream of the strut injectors and distributions obtained from one-dimensional calculations. Measured duct heat load agrees with results of the one-dimensional calculations for moderate amounts of reaction, but is underestimated when large separated regions occur near the injection location. For the parallel injection strut, good agreement is obtained between the shape of the injected fuel distribution inferred from gas sample measurements at the duct exit and the distribution calculated with a multiple-jet mixing theory. The overall fraction of injected fuel reacted in the multiple-jet calculation closely matches the amount of fuel reaction necessary to match static pressure with the one-dimensional calculation. Gas sample measurements with the perpendicular injection strut also give results consistent with the amount of fuel reaction in the one-dimensional calculation.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7581 , L-9428
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  • 7
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    Nonreactive mixing study of a scramjet swept-strut fuel injector (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a cold-mixing investigation performed to supply combustor design information and to determine optimum normal fuel-injector configurations for a general scramjet swept-strut fuel injector. The experimental investigation was made with two swept struts in a closed duct at a Mach number of 4.4 and a nominal ratio of jet mass flow to air mass flow of 0.0295, with helium used to simulate hydrogen fuel. Four injector patterns were evaluated; they represented the range of hole spacing and the ratio of jet dynamic pressure to free-stream dynamic pressure. Helium concentration, pitot pressure, and static pressure in the downstream mixing region were measured to generate the contour plots needed to define the mixing-region flow field and the mixing parameters. Experimental results show that the fuel penetration from the struts was less than the predicted values based on flat-plate data; but the mixing rate was faster and produced a mixing length less than one-half that predicted.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TN-D-8069 , L-10383
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  • 8
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    Combustion of hydrogen in a two-dimensional duct with step fuel injectors (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation of the combustion of hydrogen perpendicularly injected from step fuel injectors into a Mach 2.72, 2100 K vitiated test gas was conducted. The model simulated the flow between the center and side struts of an integrated scramjet module at Mach 7 flight and an altitude of 29 km. Parametric variation included equivalence ratio, fuel dynamic pressure ratio, and area distribution of the model. The overall area ratio of the model was held constant at 2.87. The data analysis indicated that no measurable improvement in mixing or combustion efficiency was obtained by varying the fuel dynamic pressure ratio from 0.79 to 2.45. Computations indicated approximately 80 percent of the fuel was mixed so that it could react; however, only approximately 50 percent of the mixed fuel actually reacted in two test configurations, and 74 percent in later tests where less area expansion of the flow occurred.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1159 , L-11981
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  • 9
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    Laser velocimetry technique applied to the Langley 0.3 meter transonic cryogenic tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low power laser velocimeter operating in the forward scatter mode was used to measure free stream mean velocities in the Langley 0.3 Meter Transonic Cryogenic Tunnel. Velocity ranging from 51 to 235 m/s was measured. Measurements were obtained for a variety of nominal tunnel conditions: Mach numbers from 0.20 to 0.77, total temperatures from 100 to 250 K, and pressures from 101 to 152 kPa. Particles were not injected to augment the existing Mie scattering materials. Liquid nitrogen droplets were the existing liqht scattering material. Tunnel vibrations and thermal effects had no detrimental effects on the optical system.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-81913 , L-14244
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  • 10
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    Atomization, drop size, and penetration for cross-stream water injection at high-altitude reentry conditions with application to the RAM C-1 and C-3 flights (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Atomization, drop size, and penetration data are presented for cross stream water injection at conditions simulating high altitude reentry (low Weber number, high static temperature, high Knudsen number, and low static pressure). These results are applied to the RAM C-1 and C-3 flights. Two primary breakup modes are considered, vapor pressure or flashing and aerodynamic atomization. Results are given for breakup boundaries and mean drop size for each of these atomization mechanisms. Both standard and flight orifice geometries are investigated. The data were obtained in both a static environment and in conventional aerodynamic facilities at Mach numbers of 4.5 and 8. The high temperature aspects of reentry were simulated in a Mach 5.5 cyanogen-oxygen tunnel with total temperature of 4500 K.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-6747 , L-8004
    Format: application/pdf
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