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  • Articles
  • Other Sources  (180)
  • NASA Technical Reports  (180)
  • Bibliography on Seismology
  • AERODYNAMICS  (125)
  • MECHANICAL ENGINEERING  (55)
  • 1980-1984  (180)
  • 1965-1969
  • 1983  (180)
Collection
  • Articles
  • Other Sources  (180)
Source
  • NASA Technical Reports  (180)
  • Bibliography on Seismology
Keywords
Years
  • 1980-1984  (180)
  • 1965-1969
Year
  • 1
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    Advanced technology exhaust nozzle development (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The requirement for greater tactical aircraft operational capabilities has led to increasing research emphasis on the refinement of engine/airframe integration methods and exhaust nozzle flexibility. A major prospective advancement in the development of these capabilities takes the form of multifunctional exhaust nozzle systems with thrust reversal and thrust vectoring features, whose operation will be shared by both airframe and powerplant control systems. Attention is presently given to the two-dimensional convergent-divergent and single expansion ramp nozzle designs, with emphasis on the variable geometry mechanical systems by which they assume cruising flight, vectoring, and thrust reversal operations. The nozzles have been wind tunnel model-tested for the cases of the F-18 fighter and a supersonic cruise configuration concept.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1286
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Stability of shock waves attached to wedges and cones (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 799, Accession no. A82-17876
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1611-161
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unsteady transonic small disturbance approximation with strong shock waves (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 797, Accession no. A82-17812
    Keywords: AERODYNAMICS
    Type: (ISSN 0001-1452)
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Double arch mirror study (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development of a method of mounting light weight glass mirrors for astronomical telescopes compatible with the goals of the Shuttle Infrared Telescope Facility (SIRTF) was investigated. A 20 in. diameter double arch lightweight mirror previously fabricated was modified to use a new mount configuration. This mount concept was developed and fabricated. The mounting concept of the double mounting mirror is outlined. The modifications made to the mirror, fabrication of the mirror mount, and room temperature testing of the mirror and mount and the extension of the mirror and mount concept to a full size (40 in. diameter) primary mirror for SIRTF are discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589 , NAS 1.26:166589
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Double arch mirror study. Part 1: Preliminary engineering report (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the proposed design, the NASA AMES 20-in double arch mirror is supported by three clamp and flexure assemblies. The mirror clamp consists of a T-shaped Invar-36 member that goes into a similarly shaped socket in the back of the mirror. The mirror socket is made oversize and contacts the clamp only along the conical surface. The clamp is preloaded by a spring washer and pulls the mirror into contact with the flexure. The clamp is then inserted into the mirror socket through a cutout, is rotated 90 deg, and is then pinned in place. Loading conditions considered in socket design are discussed as well as stress in the socket and clamp. Flexure geometry and stress are examined as well as the effects of flexure error and of mirror cell error.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589-PT-1 , NAS 1.26:166589-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Convair 990 transonic flow-field simulation about the forward fuselage (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional, viscous flow code was used to calculate the transonic flow about the forebody of the Convair CV-990 (Galileo II) research aircraft stationed at NASA Ames Research Center. The computations were used to determine the location for a differential pressure system. In addition, attitude sensor placements were verified. These instruments comprise a meteorological measurement system, which will be used for global determination of three-dimensional wind data. The code solves the thin layer form of the Reynolds-averaged Navier-Stokes equations using an implicit numerical procedure. The governing equations are written in a generalized, nonorthogonal coordinate system, and are cast in a strong conservation law form. Laminar boundary layer results are presented for free stream Mach number of 0.8 and angles of attack of zero and 2 deg. Use of this computational tool reduced the development time for the location of the sensors and aided in the optimal placement on the aircraft of these devices.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1785
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Calculation of a simulated 3-D high speed inlet using the Navier-Stokes equations (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A hybrid numerical algorithm, developed to solve the full three-dimensional Navier-Stokes equations, is applied to the computation of the flowfield in a simulated three-dimensional high speed aircraft inlet at a Mach number of 2.5 and Reynolds number of 1.4 x 10 to the 7th based on inlet length. The numerical algorithm incorporates a coordinate transformation in order to handle general flow geometries, and utilizes the algebraic turbulent eddy viscosity model of Baldwin and Lomax. The hybrid algorithm has been vectorized on the CDC CYBER 203 computer using the SL/1 vector programming language developed at NASA Langley. The computed results are compared with experimental measurements of the ramp and cowl static pressures, and boundary layer pitot profiles. The results are also compared with a previous two-dimensional Navier-Stokes computation of the same configuration. The agreement with the experimental data is generally good; however, additional improvements in turbulence modeling are needed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1165
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Space applications of Automation, Robotics And Machine Intelligence Systems (ARAMIS). Volume 3, phase 2: Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The field of telepresence is defined, and overviews of those capabilities that are now available, and those that will be required to support a NASA telepresence effort are provided. Investigation of NASA's plans and goals with regard to telepresence, extensive literature search for materials relating to relevant technologies, a description of these technologies and their state of the art, and projections for advances in these technologies are included. Several space projects are examined in detail to determine what capabilities are required of a telepresence system in order to accomplish various tasks, such as servicing and assembly. The key operational and technological areas are identified, conclusions and recommendations are made for further research, and an example developmental program leading to an operational telepresence servicer is presented.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3736 , NAS 1.26:3736 , SSL-32-83-VOL-3-PHASE-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    High Reynolds number tests of the CAST 10-2/DOA 2 airfoil in the Langley 0.3-meter transonic cryogenic tunnel, phase 1 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of an advanced technology airfoil, the CAST 10-2/DOA 2, was conducted in the Langley 0.3 meter Transonic Cryogenic Tunnel (0.3 m TCT). This was the first of a series of tests conducted in a cooperative National Aeronautics and Space Administration (NASA) and the Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt e. V. (DFVLR) airfoil research program. Test temperature was varied from 280 K to 100 K to pressures from slightly above 1 to 5.8 atmospheres. Mach number was varied from 0.60 to 0.80, and the Reynolds number (based on airfoil chord) was varied from 4 x 10 to the 8th power to 45 x 10 to the 6th power. This report presents the experimental aerodynamic data obtained for the airfoil and includes descriptions of the airfoil model, the 0.3 m TCT, the test instrumentation, and the testing procedures.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84620 , NAS 1.15:84620
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Space Applications of Automation, Robotics and Machine Intelligence Systems (ARAMIS), phase 2. Volume 2: Telepresence project applications (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The field of telepresence is defined and overviews of those capabilities that are now available, and those that will be required to support a NASA telepresence effort are provided. Investigation of NASA' plans and goals with regard to telepresence, extensive literature search for materials relating to relevant technologies, a description of these technologies and their state of the art, and projections for advances in these technologies over the next decade are included.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3735 , NAS 1.26:3735 , SSL-31-83
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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