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  • 1975-1979  (9)
  • 1965-1969  (3)
  • 1
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    An experimental and computational investigation of the flow field about a transonic airfoil in supercritical flow with turbulent boundary-layer separation (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A combined experimental and computational research program is described for testing and guiding turbulence modeling within regions of separation induced by shock waves incident in turbulent boundary layers. Specifically, studies are made of the separated flow the rear portion of an 18%-thick circular-arc airfoil at zero angle of attack in high Reynolds number supercritical flow. The measurements include distributions of surface static pressure and local skin friction. The instruments employed include highfrequency response pressure cells and a large array of surface hot-wire skin-friction gages. Computations at the experimental flow conditions are made using time-dependent solutions of ensemble-averaged Navier-Stokes equations, plus additional equations for the turbulence modeling.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-73157 , A-6690
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Evaluation of mean and turbulent velocity measurements in subsonic accelerated boundary layers (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploratory measurements of the mean and turbulent flow in the wall boundary layer of a 15.5- by 10.2-cm channel were obtained as part of an instrumentation development program for measurements in compressible flow. Mean surface and flow-field surveys were obtained at channel Mach numbers ranging from 0.2 to 0.9. The mean velocity distributions were obtained with total pressure probes and a laser velocimeter. At a channel Mach number of 0.2, several types of hot-wire probes were used to obtain both velocity fluctuations and Reynolds shear-stress results.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-62488 , A-6278
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Torquing preload in a lubricated bolt (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The tension preload obtained by torquing a 7/8 in. diam UNC high strength bolt was determined for lubricated and dry conditions. Consistent preload with a variation of + or - 3% was obtained when the bolt head area was lubricated prior to each torque application. Preload tensions nearly 70% greater than the value predicted with the commonly used formula occurred with the lubricated bolt. A reduction to 39% of the initial preload was observed during 50 torque applications without relubrication. Little evidence of wear was noted after 203 cycles of tightening.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-TM-78501 , A-7503
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Convective heat transfer to the Ames M2 and M2F2 lifting entry vehicles (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Convective heat transfer characteristics of M2 and M2-F2 lifting entry vehicles
    Keywords: AIRCRAFT
    Type: NASA-TM-X-1691
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Steady and unsteady transonic flow (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation of the transonic flow over a circular arc airfoil was conducted to obtain basic information for turbulence modeling of shock-induced separated flows and to verify numerical computer codes which are being developed to simulate such flows. The investigation included the employment of a laser velocimeter to obtain data concerning the mean velocity, the shear stress, and the turbulent kinetic energy profiles in the flowfield downstream of the airfoil midchord where the flow features are more complex. Depending on the free-stream Mach number, the flowfield developed was either steady with shock-wave-induced separation extending from the foot of the shock wave to beyond the trailing edge or unsteady with a periodic motion also undergoing shock-induced separation. The experimental data were compared with the results of numerical simulations in which a computer code was employed that solved the time-dependent Reynolds' averaged compressible Navier-Stokes equations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-160 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    An experimental and computational investigation of the flow field about a transonic airfoil in supercritical flow with turbulent boundary-layer separation (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A combined experimental and computational research program for testing and guiding turbulence modeling within regions of separation induced by shock waves incident on turbulent boundary layers is described. Specifically, studies are made of the separated flow over the rear portion of an 18%-thick circular-arc airfoil at zero angle of attack in high Reynolds number supercritical flow. The measurements include distributions of surface static pressure and local skin friction. The instruments employed include high-frequency response pressure cells and a large array of surface hot-wire skin-friction gages. Computations at the experimental flow conditions are made using time-dependent solutions of ensemble-averaged Navier-Stokes equations, plus additional equations for the turbulence modeling.
    Keywords: AERODYNAMICS
    Type: ICAS PAPER 76-15 , Congress; Oct 03, 1976 - Oct 08, 1976; Ottawa; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Inertia diaphragm pressure transducer Patent (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design and development of inertia diaphragm pressure transducer
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Evaluation of mean and turbulent velocity measurements in subsonic accelerated boundary layers (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploratory measurements of the mean and turbulent flow in the wall boundary layer of a 15.2- by 10.2-cm channel were obtained as part of an instrumentation development program for measurements in compressible flow. Mean surface and flow field surveys were obtained at channel Mach numbers ranging from 0.2 to 0.9. The mean velocity distributions were obtained with total pressure probes and a laser velocimeter. At a channel Mach number of 0.2, several types of hot-wire probes were used to obtain both velocity fluctuations and Reynolds shear-stress results.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8367 , A-6278
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Application of laser velocimetry to an unsteady transonic flow (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Measurements of mean velocity, turbulent kinetic energy, and turbulent shear stress have been obtained in an unsteady but periodic flow. Polystyrene spheres, 0.35-0.55 microns in diameter, were injected into the tunnel settling chamber to seed the flow for a laser velocimeter. Synchronized counters together with an encoding interface and digital-to-analog converters were used to record the data on an analog tape recorder. Profiles of velocity and turbulence quantities are presented for several times during the periodic flow.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ICIASF ''79; International Congress on Instrumentation in Aerospace Simulation Facilities; Sep 24, 1979 - Sep 26, 1979; Monterey, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    A 500,000 sample per second digital recorder for the Ames electric arc shock tunnel. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Digital data acquisition system with ultrahigh sampling rate for Ames electric arc shock tunnel, describing analog to digital conversion, data storage, system performance, etc
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: ICIASF ''69, INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES; May 05, 1969 - May 08, 1969; FARMINGDALE, NY
    Format: text
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    NASA TECHNICAL REPORTS
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