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  • AERODYNAMICS  (93)
  • AIRCRAFT PROPULSION AND POWER  (65)
  • AEROSPACE MEDICINE  (52)
  • Aircraft Design, Testing and Performance
  • 1975-1979  (211)
  • 1950-1954
  • 1940-1944
  • 1975  (211)
Collection
Keywords
Years
  • 1975-1979  (211)
  • 1950-1954
  • 1940-1944
Year
  • 1
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    An investigation of several numerical procedures for time-asymptotic compressible Navier-Stokes solutions (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The status of an investigation of four numerical techniques for the time-dependent compressible Navier-Stokes equations is presented. Results for free shear layer calculations in the Reynolds number range from 1000 to 81000 indicate that a sequential alternating-direction implicit (ADI) finite-difference procedure requires longer computing times to reach steady state than a low-storage hopscotch finite-difference procedure. A finite-element method with cubic approximating functions was found to require excessive computer storage and computation times. A fourth method, an alternating-direction cubic spline technique which is still being tested, is also described.
    Keywords: AERODYNAMICS
    Type: Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 437-468
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Applications of Doppler ultrasound in clinical vascular disease (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Doppler ultrasound has become the most useful and versatile noninvasive technique for objective evaluation of clinical vascular disease. Commercially available continuous-wave instruments provide qualitative and quantitative assessment of venous and arterial disease. Pulsed Doppler ultrasound was developed to provide longitudinal and transverse cross-sectional images of the arterial lumen with a resolution approaching that of conventional X-ray techniques. Application of Doppler ultrasound in venous, peripheral arterial, and cerebrovascular diseases is reviewed.
    Keywords: AEROSPACE MEDICINE
    Type: Soc. of Photo-Opt. Instrumentation Engrs. Cardiovascular Imaging and Image Processing; p 65-72
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A study of casing treatment stall margin improvement phenomena (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of a program of experimental and analytical research in casing treatments over axial compressor rotor blade tips are presented. Circumferential groove, axial-skewed slot and blade angle slot treatments were tested at low speeds. With the circumferential groove treatment the stalling flow was reduced 5.8% at negligible efficiency sacrifice. The axial-skewed slot treatment improved the stalling flow by 15.3%; 1.8 points in peak efficiency were sacrificed. The blade angle slot treatment improved the stalling flow by 15.0%; 1.4 points in peak efficiency were sacrificed. The favorable stalling flow situations correlated well with observations of higher-than-normal surface pressures on the rotor blade pressure surfaces in the tip region, and with increased maximum diffusions on the suction surfaces. Annulus wall pressure gradients, especially in the 50 to 75% chord region, are also increased and blade surface pressure loadings are shifted toward the trailing edge for treated configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 75-GT-60 , American Society of Mechanical Engineers, Gas Turbine Conference and Products Show; Mar 02, 1975 - Mar 06, 1975; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Development and evaluation of a new method for predicting aircraft buffet response (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The buffet prediction method uses rigid wind tunnel model fluctuating pressure data to form a buffet forcing function. The response is then calculated with a mathematical dynamic model of the airplane developed for gust response analysis. By including the extremes of phasing and contribution of symmetric and antisymmetric airplane responses, the upper and lower bounds are established for buffet response. F-111A flight test data show good agreement with predicted bounds for a variety of flight conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-69 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 5
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    Some results of medical studies of Voskhod 2 spacecraft crew members (1975)
    In:  CASI
    Details
    Publication Date: 2006-05-09
    Description: Clinical and psychological examinations of the astronauts before, during and after space flight established fluctuations in heart rate, blood circulation, metabolism and sensorimotor reactions that disappeared completely one month after flight.
    Keywords: AEROSPACE MEDICINE
    Type: Weightlessness: Med. and Biol. Res. (NASA-TT-F-16105); p 116-128
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Apollo command and service module and lunar module environmental control systems (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The environmental control systems and system requirements of the Apollo command service module and the lunar module are described. The overall performance of both systems during the Apollo program is discussed. Other topics covered include: dust control, EVA provisions, Apollo 13 emergency, component redundancy, modular construction, and subatmospheric design.
    Keywords: AEROSPACE MEDICINE
    Type: Biomedical Results of Apollo; p 517-543
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Mach and Reynolds number effects on turbulent skin friction reduction by injection (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The investigation reported is concerned with questions regarding a possible Mach number influence on skin friction reduction caused by injection. The investigation shows that data considered by Danberg (1967) for the no-blowing skin friction coefficient are in error. Accurate profiles and local skin friction coefficient values are obtained when the influence of low Reynolds number amplification in the outer region of the boundary layer is included in a calculation method.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 12; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Digital image processing of vascular angiograms (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: A computer image processing technique was developed to estimate the degree of atherosclerosis in the human femoral artery. With an angiographic film of the vessel as input, the computer was programmed to estimate vessel abnormality through a series of measurements, some derived primarily from the vessel edge information and others from optical density variations within the lumen shadow. These measurements were combined into an atherosclerosis index, which was found to correlate well with both visual and chemical estimates of atherosclerotic disease.
    Keywords: AEROSPACE MEDICINE
    Type: Soc. of Photo-Opt. Instrumentation Engrs. Cardiovascular Imaging and Image Processing; p 159-162
    Format: text
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  • 9
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    Fire safety evaluation of aircraft lavatory and cargo compartments (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Large-scale aircraft lavatory and cargo compartment fire tests are described. Tests were conducted to evaluate the effectiveness of these compartments to contain fire and smoke. Two tests were conducted and are detailed. Test 1 involved a production Boeing 747 lavatory of the latest design installed in an enclosure outside the aircraft, to collect gases and expose animals to these gases. Results indicate that the interior of the lavatory was completely burned, evolving smoke and combustion products in the enclosure. Test 2 involved a simulated Douglas DC-10 cargo compartment retro-fitted with standard fiberglass liner. The fire caused excessive damage to the liner and burned through the ceiling in two areas. Test objectives, methods, materials, and results are presented and discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62471 , A-6235
    Format: application/pdf
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  • 10
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    Wind tunnel investigation of a large-scale upper surface blown-flap model having four engines (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigations were conducted in the Ames 40- by 80-Foot Wind Tunnel to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an upper surface blown flap system. The model had a 25 deg swept wing of aspect ratio 7.28 and four turbofan engines. The lift of the flap system was augmented by turning the turbofan exhaust over the Coanda surface. Results were obtained for several flap deflections with several wing leading-edge configurations at jet momentum coefficients from 0 to 4.0. Three-component longitudinal data are presented with four engines operating. In addition, longitudinal and lateral data are presented with an engine out. The maximum lift and stall angle of the four engine model were lower than those obtained with a two engine model that was previously investigated. The addition of the outboard nacelles had an adverse effect on these values. Efforts to improve these values were successful. A maximum lift of 8.8 at an angle-of-attack of 27 deg was obtained with a jet thrust coefficient of 2 for the landing flap configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62419 , A-6003
    Format: application/pdf
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