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  • 1
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    Experimental investigation of a simulated LOX injector flow field and other nonintrusive measurement efforts (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Efforts to improve the characteristics of fuel-oxidizer mixing in liquid rocket combustors have lead to a swirl element design for a liquid oxygen injector which is being considered for use on the STME. For the design which is the subject of this investigation, the oxygen enters the injector element perpendicular to the injector axis and nearly tangent to the circular injector wall. This swirl element is at one end of a tube and the injector exit is at the other. This geometric configuration creates a plume in the shape of a conical sheet. This sheet is either primarily contiguous liquid or droplets depending on the pressure drop in the injector and the distance from the injector exit. Probe-based devices such as two-dimensional grid patternators have been used to investigate simulated LOX injector flow fields (Hulka). The primary work described herein is an effort to use optical techniques to investigate the plume of a swirl injector element. For this investigation, a high pressure (500 psig) cold flow test facility was constructed. Water was used as the LOX simulate and air pressure was used to drive the injector flow field. Laser-induced fluorescence (LIF) from dye seeded into the water was used to obtain quantitative measurements of the time-averaged water concentration distribution in the plume. Scattered laser light and LIF were used for time averaged plume visualization and scattered light from a strobe with a 1 microsecond pulse was used for time-resolved plume visualization. During the Summer Faculty Fellowship for which this report was developed, an additional effort, unrelated to the swirl injector investigation, was made to resolve fluctuations in the combustion product composition in the exhaust of a hybrid rocket motor. A brief description of this effort is included herein.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., 1992 NASA(ASEE Summer Faculty Fellowship Program; 5 p
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  • 2
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    A Detailed Investigation of Staged Normal Injection into a Mach 2 Flow (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A study of the staged injection of two jets of air behind a rearward facing step into a Mach 2 flow was performed using the SPARK 3-D Navier-Stokes code. Calculated mole fraction distributions were compared with an extensive set of planar mole fraction measurements made with a laser induced iodine fluorescence technique. A statistical measure, the standard deviation, was used to help assess agreement between calculation and experiment. Overall, good agreement was found between calculated and measured values. Generally, agreement was better in the far field of the injectors. The effect of grid resolution was investigated by calculating solutions on grids of 60,000, 200,000, and 450,000 points. Differences in the solutions on the two finer grids were small. However, the mole fraction distributions were distinguishable. The effect of turbulence modeling was investigated by employing three different algebraic models for the jet turbulence: the Baldwin-Lomax model, the Prandtl mixing length model, and the Eggers mixing length model. Overall, the Eggers mixing length model was found to be superior for this case. Finally, the effect of the jet exit conditions was examined. A recently proposed Mach number distribution at the jet exit was found to slightly improve agreement between measurement and calculation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: 27th JANNAF Combustion Subcommittee Meeting; Volume 3; 115-129
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  • 3
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    Planar temperature measurement in compressible flows using laser-induced iodine fluorescence (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A laser-induced iodine fluorescence technique that is suitable for the planar measurement of temperature in cold nonreacting compressible air flows is investigated analytically and demonstrated in a known flow field. The technique is based on the temperature dependence of the broadband fluorescence from iodine excited by the 514-nm line of an argon-ion laser. Temperatures ranging from 165 to 245 K were measured in the calibration flow field. This technique makes complete, spatially resolved surveys of temperature practical in highly three-dimensional, low-temperature compressible flows.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optics Letters (ISSN 0146-9592); 16; 106-108
    Format: text
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  • 4
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    Injectant mole-fraction imaging in compressible mixing flows using planar laser-induced iodine fluorescence (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A technique is described for imaging the injectant mole-fraction distribution in nonreacting compressible mixing flow fields. Planar fluorescence from iodine, seeded into air, is induced by a broadband argon-ion laser and collected using an intensified charge-injection-device array camera. The technique eliminates the thermodynamic dependence of the iodine fluorescence in the compressible flow field by taking the ratio of two images collected with identical thermodynamic flow conditions but different iodine seeding conditions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optics Letters (ISSN 0146-9592); 14; 850-852
    Format: text
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  • 5
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    In-flight demonstration of a Real-Time Flush Airdata Sensing (RT-FADS) system (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A prototype real-time flush airdata sensing (RT-FADS) system has been developed and flight tested at the NASA Dryden Flight Research Center. This system uses a matrix of pressure orifices on the vehicle nose to estimate airdata parameters in real time using nonlinear regression. The algorithm is robust to sensor failures and noise in the measured pressures. The RT-FADS system has been calibrated using inertial trajectory measurements that were bootstrapped for atmospheric conditions using meteorological data. Mach numbers as high as 1.6 and angles of attack greater than 45 deg have been tested. The system performance has been evaluated by comparing the RT-FADS to the ship system airdata computer measurements to give a quantitative evaluation relative to an accepted measurement standard. Nominal agreements of approximately 0.003 in Mach number and 0.20 deg in angle of attack and angle of sideslip have been achieved.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TM-104314 , H-2053 , NAS 1.15:104314
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  • 6
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    Covariant noether identities in covariant field theories (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Covariant Noether identities in covariant field theories
    Keywords: PHYSICS, GENERAL
    Type: NASA-CR-78874 , R-305
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  • 7
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    Planar measurement of flow field parameters in a nonreacting supersonic combustor using laser-induced iodine fluorescence (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A nonintrusive optical technique, laser-induced iodine fluorescence, has been used to obtain planar measurements of flow field parameters in the supersonic mixing flow field of a nonreacting supersonic combustor. The combustor design used in this work was configured with staged transverse sonic injection behind a rearward-facing step into a Mach 2.07 free stream. A set of spatially resolved measurements of temperature and injectant mole fraction has been generated. These measurements provide an extensive and accurate experimental data set required for the validation of computational fluid dynamic codes developed for the calculation of highly three-dimensional combustor flow fields.
    Keywords: LASERS AND MASERS
    Type: AIAA PAPER 90-0162
    Format: text
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  • 8
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    Transverse injection into Mach 2 flow behind a rearward-facing step - A 3-D, compressible flow test case for hypersonic combustor CFD validation (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A spatially-complete data set of the important primitive flow variables is presented for the complex, nonreacting, 3D unit combustor flow field employing transverse injection into a Mach 2 flow behind a rearward-facing step. A unique wind tunnel facility providing the capability for iodine seeding was built specifically for these measurements. Two optical techniques based on laser-induced-iodine fluorescence were developed and utilized for nonintrusive, in situ flow field measurements. LDA provided both mean and fluctuating velocity component measurements. A thermographic phosphor wall temperature measurement technique was developed and employed. Data from the 2D flow over a rearward-facing step and the complex 3D mixing flow with injection are reported.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-5071
    Format: text
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  • 9
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    The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained from a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircraft research station at Wallops Island, Va. The results include the longitudinal stability derivatives, control effectiveness, drag characteristics, and control-surface hinge-moment characteristics for a Mach number range of 0.7 to 1.45.
    Type: NACA-RM-L50I27
    Format: application/pdf
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  • 10
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    Column and Plate Compressive Strengths of Aircraft Structural Materials: 24S-T Aluminum-alloy Sheet (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-190 , NACA-ARR-L5F01
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