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  • INSTRUMENTATION AND PHOTOGRAPHY  (19)
  • AIRCRAFT PROPULSION AND POWER  (14)
  • 1975-1979  (33)
  • 1
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    CAMAC and NIM systems in the space program (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The CAMAC and NIM instrumentation systems were developed originally to serve the needs of nuclear research institutions in Europe and North America. CAMAC and NIM are currently considered in several studies at the systems level conducted by NASA and ESRO groups. NIM and CAMAC studies for applications related to the space shuttle are discussed along with the advantages provided by aspects of modularization and standardization, a use of NIM and CAMAC equipment in connection with a group of astrophysics experiments, and questions of cost effectiveness.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Pediatrics (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The utilization of the Lixiscope in pediatrics was investigated. The types of images that can presently be obtained are discussed along with the problems encountered. Speculative applications for the Lixiscope are also presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Preliminary Appl. and Evaluation Results. Lixiscope; p 51-59
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Portable high-resolution laser monochromator-interferometer with multichannel electronic readout (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A high-resolution 0.4-m monochromator is described for use in wavelength diagnosis of tunable pulsed and CW laser sources in the 3000-10,000-A region. The f/20 design uses an echelle grating in an over-and-under Ebert configuration with a scanned photodiode array to provide a real-time multichannel display of spectral output. Absolute wavelength may be determined to 0.1 A with the monochromator, and a Fabry-Perot interferometer attachment extends linewidth measurement capability to 0.01 A or better. Spectra are displayed on a storage oscilloscope, and calculation of laser parameters is explained. The instrument measures 70 cm long x 15 cm wide x 20 cm high.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 18; Dec. 15
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Pressure Modulator Radiometer (PMR) tests (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The pressure modulator technique was evaluated for monitoring pollutant gases in the Earth's atmosphere of altitude levels corresponding to the mid and lower troposphere. Using an experimental set up and a 110 cm sample cell, pressure modulator output signals resulting from a range of gas concentrations in the sample cell were examined. Then a 20 cm sample cell was modified so that trace gas properties in the atmosphere could be simulated in the laboratory. These gas properties were measured using an infrared sensor.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-159175
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Airflow and thrust calibration of an F100 engine, S/N P680059, at selected flight conditions (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine, S/N P680059, was conducted to study airframe propulsion system integration losses in turbofan-powered high-performance aircraft. The tests were conducted with and without thrust augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. The resulting corrected airflow data generalized into one curve with corrected fan speed while corrected gross thrust increased as simulated flight conditions increased. Overall agreement between measured data and computed results was 1 percent for corrected airflow and -1 1/2 percent for gross thrust. The results of an uncertainty analysis are presented for both parameters at each simulated flight condition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1069 , E-9257
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Single stage, low noise, advanced technology fan. Volume 1: Aerodynamic design (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design for a half-scale fan vehicle, which would have application on an advanced transport aircraft, is described. The single stage advanced technology fan was designed to a pressure ratio of 1.8 at a tip speed of 503 m/sec 11,650 ft/sec). The fan and booster components are designed in a scale model flow size convenient for testing with existing facility and vehicle hardware. The design corrected flow per unit annulus area at the fan face is 215 kg/sec sq m (44.0 lb m/sec sq ft) with a hub-tip ratio of 0.38 at the leading edge of the fan rotor. This results in an inlet corrected airflow of 117.9 kg/sec (259.9 lb m/sec) for the selected rotor tip diameter if 90.37 cm (35.58 in.). The variable geometry inlet is designed utilizing a combination of high throat Mach number and acoustic treatment in the inlet diffuser for noise suppression (hybrid inlet). A variable fan exhaust nozzle was assumed in conjunction with the variable inlet throat area to limit the required area change of the inlet throat at approach and hence limit the overall diffusion and inlet length. The fan exit duct design was primarily influenced by acoustic requirements, including length of suppressor wall treatment; length, thickness and position on a duct splitter for additional suppressor treatment; and duct surface Mach numbers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134801 , R76AEG257-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Altitude performance of a low-noise-technology fan in a turbofan engine with and without a sound suppressing nacelle (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test variables were inlet Reynolds number index (0.2 to 0.5), flight Mach number (0.2 to 0.8), and flow distortion (tip radial and combined circumferential - tip radial patterns). Results are limited to fan bypass and overall engine performance. There were no discernible effects of Reynolds number on fan performance. Increasing flight Mach number shifted the fan operating line such that pressure ratio decreased and airflow increased. Inlet flow distortion lowered stall margin. For a Reynolds number index of 0.2 and flight Mach number of 0.54, the sound suppressing nacelle lowered fan efficiency three points and increased specific fuel consumption about 10 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3385 , E-8592
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Altitude calibration of an F100, S/N P680063, turbofan engine (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airflow and thrust calibration of an F100 engine was conducted in coordination with a flight test program to study airframe-propulsion system integration characteristics of turbofan-powered high-performance aircraft. The tests were conducted with and without augmentation for a variety of simulated flight conditions with emphasis on the transonic regime. Test results for all conditions are presented in terms of corrected airflow and corrected gross thrust as functions of corrected fan speed for nonaugmented power and an augmented thrust ratio as a function of fuel-air ratio for augmented power. Comparisons of measured and predicted data are presented along with the results of an uncertainty analysis for both corrected airflow and gross thrust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1228 , E-9355
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Single stage, low noise, advanced technology fan. Volume 4: Fan aerodynamics. Section 2: Overall and blade element performance data tabulations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N77-17060.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134893 , R76AEG566-VOL-4
    Format: application/pdf
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  • 10
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    Single-stage, low-noise, advanced technology fan. Volume 4: Fan aerodynamics. Section 1: Results and analysis (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test results at design speed show fan total pressure ratio, weight flow, and adiabatic efficiency to be 2.2, 2.9, and 1.8% lower than design goal values. The hybrid acoustic inlet (which utilizes a high throat Mach number and acoustic wall treatment for noise suppression) demonstrated total pressure recoveries of 98.9% and 98.2% at takeoff and approach. Exhaust duct pressure losses differed between the hardwall duct and treated duct with splitter by about 0.6% to 2.0% in terms of fan exit average total pressure (depending on operating condition). When the measured results were used to estimate pressure losses, a cruise sfc penalty of 0.68%, due to the acoustically treated duct, was projected.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134892 , R76AEG565-VOL-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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