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  • 1
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    Wideband low noise maser amplifiers (1970)
    In:  CASI
    Details
    Publication Date: 2006-04-25
    Description: Iron doped rutile wideband maser amplifier with low signal-to-noise ratio
    Keywords: MASERS
    Type: NIFICANT ACCOMPLISHMENTS IN SCI. AND TECHNOL. AT GODDARD SPACE FLIGHT CENTER 1970; P 337-339
    Format: text
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  • 2
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    Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 143-156
    Format: text
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  • 3
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    A new type of powder maser (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Maser amplifier with nonoriented Fe-doped rutile powder as active material, observing broad absorption bands under magnetic field
    Keywords: MASERS
    Type: ; YAL SOCIETY (
    Format: text
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  • 4
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    Mariner Mars 1969 infrared spectrometer - Gas delivery system and Joule-Thomson cryostat. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cryogenics; 13; Sept
    Format: text
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  • 5
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    Energy storage using high pressure electrolysis and methods for reconversion (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Theoretical and experimental studies on high pressure electrolysis producing hydrogen and oxygen for energy storage and reconversion are reported. Moderate temperature, high pressure hydrogen/oxygen fuel cells with nickel electrodes are investigated for effects of pressure, temperature, and membrane porosity. Test results from an aphodid burner turbine generator combination obtained 40 percent kilowatt hours out of the fuel cell divided by kilowatt hours into the electrolyzer. It is concluded that high pressure hydrogenation of organic materials can be used to synthesize hydrozenes and methanes for making synthetic vehicular fuels.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA. Lewis Res. Center Wind Energy Conversion Systems; p 123-129
    Format: application/pdf
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  • 6
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    Method for forming pyrrone molding powders and products of said method (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The formation of pyrrone resins of the ladder or semiladder structure is described. The technique involves initial formation of fully cyclized prepolymers having an average degree of polymerization of about 1.5, one with acidic terminal groups, another with amine terminal groups. Thereafter the prepolymers are intimately admixed on a 1:1 stoichiometric basis. The resulting powder mixture is molded at elevated pressures and temperatures to form a fully cyclized resin.
    Keywords: CHEMISTRY AND MATERIALS (GENERAL)
    Format: application/pdf
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  • 7
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    Steady-state and dynamic pressure phenomena in the propulsion system of an F-111A airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests were conducted with two F-111A airplanes to study the effects of steady-state and dynamic pressure phenomena on the propulsion system. Analysis of over 100 engine compressor stalls revealed that the stalls were caused by high levels of instantaneous distortion. In 73 percent of these stalls, the instantaneous circumferential distortion parameter, k sub theta, exhibited a peak just prior to stall higher than any previous peak. The K sub theta parameter was a better indicator of stall than the distortion factor, k sub d, and the maximum-minus-minimum distortion parameter, d, was poor indicator of stall. Inlet duct resonance occurred in both F-111A airplanes and is believed to have been caused by oscillations of the normal shock wave from an internal to an external position. The inlet performance of the two airplanes was similar in terms of pressure recovery, distortion, and turbulence, and there was good agreement between flight and wind-tunnel data up to a Mach number of approximately 1.8.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-7328 , H-741
    Format: application/pdf
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  • 8
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    Luminosity functions for K giant stars derived from the two-micron sky survey. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Description of a method for determining either the space density or the luminosity function from star counts covering large areas of sky. Space density is assumed to vary only in the direction perpendicular to the galactic plane. The method extends that derived for use with the star counts in the Selected Areas by allowing for an integration over a wide and continuous range of galactic latitudes, and is therefore applicable to surveys where the number of stars per square degree is small but the area surveyed is an appreciable fraction of the sky. The catalog (IRC) produced from the 2-micron sky survey at Caltech is such a survey. Application of the method to a selection of IRC stars dominated by K giants shows that if these stars obey Oort's determination of their normalized space density perpendicular to the galactic plane than the dispersion of their 2.2-micron luminosity distribution must be large - i.e., on the order of plus or minus 1.0 min within a single spectral subtype. This result is in accord with conclusions recently set forth by Jung (1970).
    Keywords: SPACE SCIENCES
    Type: Astronomical Society of the Pacific; vol. 85
    Format: text
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  • 9
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    Measured microwave scattering cross sections of three meteorite specimens (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three meteorite specimens were used in a microwave scattering experiment to determine the scattering cross sections of stony meteorites and iron meteorites in the frequency range from 10 to 14 GHz. The results indicate that the stony meteorites have a microwave scattering cross section that is 30 to 50 percent of their projected optical cross section. Measurements of the iron meteorite scattering were inconclusive because of specimen surface irregularities.
    Keywords: SPACE SCIENCES
    Type: NASA-TN-D-7064 , G-1073
    Format: application/pdf
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  • 10
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    C-5A/orbiter wind tunnel testing and analysis: Piggyback ferry (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel testing and analytical studies of the feasibility of ferrying the NASA Shuttle Orbiter on the C-5A in a piggyback mode have been accomplished. Testing was conducted in the 8x12 foot low speed wind tunnel using an existing 0.0399 scale C-5A model in conjunction with a NASA 0.0405 scale Orbiter model. Six component force and moment data were measured over a range of pitch and yaw angles to determine lift and drag characteristics, lateral/directional stability characteristics and longitudinal and directional control powers. A description of the wind tunnel test program with a run schedule and the complete plotted data for all the test runs are presented. Initial emphasis was given to determining the effects of the Orbiter above the C-5A and the optimum location for minimum interference on C-5A characteristics. A comprehensive series of cruise configurations were tested including a range of Orbiter longitudinal and vertical locations, incidences, and afterbody fairings. Subsequently, a series of configurations were devised during the test program to determine means of recovering directional stability degradation due to Orbiter interference.
    Keywords: AIRCRAFT
    Type: NASA-CR-134184 , LG73ER0193
    Format: application/pdf
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