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  • Other Sources  (907)
  • MACHINE ELEMENTS AND PROCESSES  (472)
  • AERODYNAMICS  (435)
  • 1970-1974  (472)
  • 1965-1969  (434)
  • 1950-1954
  • 1935-1939
  • 1900-1904  (1)
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  • Other Sources  (907)
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  • 1
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 4: IPAD system design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The computing system design of IPAD is described and the requirements which form the basis for the system design are discussed. The system is presented in terms of a functional design description and technical design specifications. The functional design specifications give the detailed description of the system design using top-down structured programming methodology. Human behavioral characteristics, which specify the system design at the user interface, security considerations, and standards for system design, implementation, and maintenance are also part of the technical design specifications. Detailed specifications of the two most common computing system types in use by the major aerospace companies which could support the IPAD system design are presented. The report of a study to investigate migration of IPAD software between the two candidate 3rd generation host computing systems and from these systems to a 4th generation system is included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132394 , D6-60181-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 1A: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: IPAD was defined as a total system oriented to the product design process. This total system was designed to recognize the product design process, individuals and their design process tasks, and the computer-based IPAD System to aid product design. Principal elements of the IPAD System include the host computer and its interactive system software, new executive and data management software, and an open-ended IPAD library of technical programs to match the intended product design process. The basic goal of the IPAD total system is to increase the productivity of the product design organization. Increases in individual productivity were feasible through automation and computer support of routine information handling. Such proven automation can directly decrease cost and flowtime in the product design process.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132390 , D6-60181-1A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Noncontacting devices to indicate deflection and vibration of turbopump internal rotating parts (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The research is reported which was conducted to develop devices for measuring vibrations and deflections of parts, such as impellers, shafts, turbine wheels, and inducers in operating turbopumps. Three devices were developed to the breadboard stage: ultrasonic Doppler transducer, flash X-rays, and light-pipe reflectance. It was found that the X-ray technique is applicable to the shaft assembly and the turbine seal of the J-2 pump, and the light-pipe-reflectance device appears to be ideal for cryogenic pump sections.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-124208
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Radiative transport in inviscid nonadiabatic stagnation-region shock layers. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Radiative transport due to continua, molecular bands and atomic lines in inviscid nonadiabatic shock layer in stagnation region of blunt bodies
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 68-784 , THERMOPHYSICS CONFERENCE; Jun 24, 1968 - Jun 26, 1968; LOS ANGELES, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Storage and handling of cryogenic fluids (1966)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Cryogenic liquid propellant storage and handling
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Development of separable connectors for the Saturn S-IV stage (1965)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Connector development, selection, and inspection for Saturn S-IV stage propulsion system
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Contributions to the study of the characteristics of bearing noise and vibrations (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Results of experimental research on the noise and vibrations of radial ball and roller bearings are reported. Analysis of the frequency spectra disclosed dependences among vibration and noise, load, rpm and cage material. Some peculiar aspects of the frequency spectrum are also mentioned.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 131-135
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 413-426
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
    Format: text
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    NASA TECHNICAL REPORTS
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