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  • AEROSPACE MEDICINE  (60)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (42)
  • Biology
  • General Chemistry
  • 1975-1979  (120)
  • 1955-1959  (9)
  • 1975  (120)
  • 1958  (9)
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Keywords
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  • 1975-1979  (120)
  • 1955-1959  (9)
Year
  • 1
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    Full-scale upper-surface-blown flap noise (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A highly noise-suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper-surface-blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord-length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are used for correlation of the noise data. Configurations using a long flap design were 4 dB quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 750609 , Society of Automotive Engineers, Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight test investigation of the vortex wake characteristics behind a Boeing 727 during two-segment and normal ILS approaches (A joint NASA/FAA report) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests were performed to evaluate the vortex wake characteristics of a Boeing 727 aircraft during conventional and two-segment instrument landing approaches. Smoke generators were used for vortex marking. The vortex was intentionally intercepted by a Lear Jet and a Piper Comanche aircraft. The vortex location during landing approach was measured using a system of phototheodolites. The tests showed that at a given separation distance there are no readily apparent differences in the upsets resulting from deliberate vortex encounters during the two types of approaches. The effect of the aircraft configuration on the extent and severity of the vortices is discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-62398 , FAA-NA-75-151
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Hematology and immunology studies (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The hematology and immunology program conducted in support of the Apollo missions was designed to acquire specific laboratory data relative to the assessment of the health status of the astronauts prior to their commitment to space flight. A second objective was to detect and identify any alterations in the normal functions of the immunohematologic systems which could be attributed to space flight exposure, and to evaluate the significance of these changes relative to man's continuing participation in space flight missions. Specific changes observed during the Gemini Program formed the basis for the major portion of the hematology-immunology test schedule. Additional measurements were included when their contribution to the overall interpretation of the flight data base became apparent.
    Keywords: AEROSPACE MEDICINE
    Type: Biomedical Results of Apollo; p 197-226
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Oxygen cost during exercise in simulated subgravity environments (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Oxygen cost (VO2) and heart rate (HR) were determined during treadmill walking in simulated subgravity environments. The long axis of the subject's body was suspended parallel to the floor in a slow rotation room with feet aligned on the surface of a treadmill mounted 90 deg on the wall. Without rotation, the subjects were virtually weightless against the treadmill; with centrifugation, environments of 0.25, 0.5 and 1 G were simulated. Oxygen cost (open circuit) and HR (ECG) were measured during the 5th minute of walking at 3.2, 4.7 and 6.1 km/h. Similar measurements were also determined during walking at 1/2-G using the inclined plane technique. Oxygen cost per unit mass and HR were significantly reduced in all subgravity environments. However, net oxygen cost per unit weight carried and, therefore, mechanical efficiency was found to be independent of gravity. This supports the idea that the most probable cause for the decreased oxygen cost with reduced gravity is less body weight carried.
    Keywords: AEROSPACE MEDICINE
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Skylab experiment results: Hematology studies (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Studies were conducted to evaluate specific aspects of man's immunologic and hematologic systems that might be altered by or respond to the space flight environment. Biochemical functions investigated included cytogenetic damage to blood cells, immune resistance to disease, regulation of plasma and red cell volumes, metabolic processes of the red blood cell, and physicochemical aspects of red blood cell function. Measurements of hematocrit value showed significant fluctuations postflight, reflecting observed changes in red cell mass and plasma volume. The capacity of lymphocytes to respond to an in vitro mitogenic challenge was repressed postflight, and appeared to be related to mission duration. Most other deviations from earth function in these systems were minor or transient.
    Keywords: AEROSPACE MEDICINE
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Apollo gastrointestinal analysis (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fecal bile acid patterns for the Apollo 17 flight were studied to determine the cause of diarrhea on the mission. The fecal sterol analysis gave no indication of an infectious diarrhea, or specific, or nonspecific etiology occurring during the entire flight. It is assumed that the gastrointestinal problems encountered are the consequences of altered physiology, perhaps secondary to physical or emotional stress of flight.
    Keywords: AEROSPACE MEDICINE
    Type: NASA-CR-144437
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Use of dew-point detection for quantitative measurement of sweating rate (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A method of measuring sweat rate (SR) based on detection of dew point (DP) is proposed which has advantages that may be attractive to other laboratories concerned with recording SR from selected areas of skin. It is similar to other methods in that dry gas is passed through a capsule which isolates several square centimeters of skin surface. The difference is in the means of determining how much gaseous water is carried off in the effluent moist gas. The DP detector used is free of the drawbacks of previous devices. DP is obtained through the fundamental technique of determining the temperature at which condensate forms on a mirror. Variations in DP are tracked rapidly, and accurately (+ or - 0.8 C nominal, sensitivity + or - 0.05 C) over a wide range ( -40 C to +50 C) without measurable hysteresis. The detector asembly is rugged and readily opened for cleaning and inspection.
    Keywords: AEROSPACE MEDICINE
    Type: Journal of Applied Physiology; 39; Sept
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Effect of shape and size of lung and chest wall on stresses in the lung (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: To understand better the effect of shape and size of lung and chest wall on the distribution of stresses, strains, and surface pressures, we analyzed a theoretical model using the technique of finite elements. First we investigated the effects of changing the chest wall shape during expansion, and second we studied lungs of a variety of inherent shapes and sizes. We found that, in general, the distributions of alveolar size, mechanical stresses, and surface pressures in the lungs were dominated by the weight of the lung and that changing the shape of the lung or chest wall had relatively little effect. Only at high states of expansion where the lung was very stiff did changing the shape of the chest wall cause substantial changes. Altering the inherent shape of the lung generally had little effect but the topographical differences in stresses and surface pressures were approximately proportional to lung height. The results are generally consistent with those found in the dog by Hoppin et al (1969).
    Keywords: AEROSPACE MEDICINE
    Type: Journal of Applied Physiology; 39; July 197
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  • 9
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    Frequency and duration of interval training programs and changes in aerobic power (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The present study was designed to ascertain whether a training frequency of 2 days/wk for a 7- and 13-wk interval training program would produce improvement in maximal aerobic power comparable to that obtained from 7- and 13-wk programs of the same intensity consisting of 4 training days/wk. After training, there was a significant increase in maximal aerobic power that was independent of both training frequency and duration. Maximal heart rate was significantly decreased following training. Submaximal aerobic power did not change with training, but submaximal heart rate decreased significantly with greater decreases the more frequent and the longer the training.
    Keywords: AEROSPACE MEDICINE
    Type: Journal of Applied Physiology; 38; Mar. 197
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    NASA TECHNICAL REPORTS
  • 10
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    Conceptual design of reduced energy transports (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper reports the results of a conceptual design study of new, near-term fuel-conservative aircraft. A parametric study was made to determine the effects of cruise Mach number and fuel cost on the 'optimum' configuration characteristics and on economic performance. Supercritical wing technology and advanced engine cycles were assumed. For each design, the wing geometry was optimized to give maximum return on investment at a particular fuel cost. Based on the results of the parametric study, a reduced energy configuration was selected. Compared with existing transport designs, the reduced energy design has a higher aspect ratio wing with lower sweep, and cruises at a lower Mach number. It yields about 30% more seat-miles/gal than current wide-body aircraft. At the higher fuel costs anticipated in the future, the reduced energy design has about the same economic performance as existing designs.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-303 , American Institute of Aeronautics and Astronautics, Annual Meeting and Technical Display; Feb 24, 1975 - Feb 26, 1975; Washington, DC
    Format: text
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