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  • 1
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    Electromagnetic Field in Electrodeless Discharge (1971)
    American Institute of Physics
    Details
    Publication Date: 1971-12-01
    Print ISSN: 0021-8979
    Electronic ISSN: 1089-7550
    Topics: Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    Electron temperatures in several RF-generated plasmas. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Electron temperatures in several RF-generated plasmas, using air as medium
    Keywords: PHYSICS, PLASMA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Probe measurements in an electrodeless discharge. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Radial distributions of number density, electron temperature and plasma potential measured in electrodeless discharge, using symmetric and asymmetric double probes
    Keywords: PHYSICS, PLASMA
    Type: AIAA PAPER 66-194
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Probe measurements in an electrodeless discharge. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Radial distributions of number density, electron temperature and plasma potential measured in electrodeless discharge, using symmetric and asymmetric double probes
    Keywords: PHYSICS, PLASMA
    Type: AIAA PAPER 66-194 , /AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Subsonic high-angle-of-attack aerodynamic characteristics of a cone and cylinder with triangular cross sections and a cone with a square cross section (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments were conducted in the 12-Foot Pressure Wind Tunnel at Ames Research Center on three models with noncircular cross sections: a cone having a square cross section with rounded corners and a cone and cylinder with triangular cross sections and rounded vertices. The cones were tested with both sharp and blunt noses. Surface pressures and force and moment measurements were obtained over an angle of attack range from 30 deg to 90 deg and selected oil-flow experiments were conducted to visualize surface flow patterns. Unit Reynolds numbers ranged from 0.8x1,000,000/m to 13.0x1,000,000/m at a Mach number of 0.25, except for a few low-Reynolds-number runs at a Mach number of 0.17. Pressure data, as well as force data and oil-flow photographs, reveal that the three dimensional flow structure at angles of attack up to 75 deg is very complex and is highly dependent on nose bluntness and Reynolds number. For angles of attack from 75 deg to 90 deg the sectional aerodynamic characteristics are similar to those of a two dimensional cylinder with the same cross section.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84377 , A-9392 , NAS 1.15:84377
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flow visualization of inflexional instabilities on a rotating disk (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experiments were conducted on a rotating disk in water using dye to observe the formation of small vortices in the boundary layer due to the inflexional nature of the boundary layer profiles in the radial and near radial directions. Such vortices have also been detected near the leading edge of swept wings and on the windward side of fuselages at angles of attack using sublimation techniques. In the present investigation, color motion pictures at 300 frames per second were taken and the vortex spacing, angles of inclination of the vortex axes and critical Reynolds numbers were determined from these films. Secondary instabilities were also observed and analyzed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 80-0279 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A subsonic flow investigation on a research body at high angles of attack (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Tests conducted in the Ames 12-foot pressure wind tunnel on a rotating research body at angles of attack of 45 to 90 deg yielded results that were inconsistent with simple cross-flow theory. Consequently, force and pressure distribution tests along with oil and sublimation flow-visualization studies were conducted in the same tunnel on a nonrotating model to attempt to explain the behavior observed in the rotary tests. These studies indicate that at appropriate conditions of Reynolds number and angle of attack, inflectional instabilities occur in the boundary layer that materially affect separation and, hence, the aerodynamic forces. Calculations of cross-flow Reynolds numbers are made and compared with other works on inflectional instability.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 77-180 , Aerospace Sciences Meeting; Jan 24, 1977 - Jan 26, 1977; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Wind-tunnel testing with a rotary-balance apparatus to simulate aircraft spin motions (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experiments have been conducted in the Ames 12-Foot Pressure Wind Tunnel on a simple airplane-like model using a rotary-balance apparatus to simulate a steady spin motion at high angles of attack. Tests were run at Mach numbers of 0.1 and 0.25 over a wide Reynolds number range with the angle of attack varying from 45 to 90 deg. During previous tests of the same research model, some difficulties were experienced with measurement accuracy in the low-to-medium range of Reynolds number because of limitations in the sensitivity of selected force balances. For the present tests, special balances were built to provide accurate measurements of the nose and tail contributions to spin motions and improvements were made to the overall test apparatus. The results of this test, including some interesting hysteresis effects with spin rate, are described. Some of the problems associated with rotary-balance tests at high Reynolds numbers are discussed. A new large-scale rotary apparatus now nearing completion for use in the Ames 12-Foot and 11- by 11-Foot Wind Tunnels is described briefly.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Aerodynamic Testing Conference; Jun 07, 1976 - Jun 09, 1976; Arlington, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental determination of post-stall rotary derivatives for airplane-like configurations at several Reynolds numbers (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Military and civilian airplane losses due to out-of-control spin motions are significant. Knowledge of rotary coefficients is necessary to understand the cause of spin entry and to devise proper recovery techniques. An exploratory wind-tunnel investigation has been conducted on simple airplane-like configurations on a rotary sting apparatus at rotation rates up to 10 rps. Rotary coefficients have been measured at unit Reynolds numbers from 2,000,000 to 24,600,000 per m and at angles of attack from 45 to 90 deg. Results show that the aerodynamic characteristics at steady spin rates are highly dependent on both spin rate and Reynolds number.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 75-171 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    The investigation of the flow about general fuselage shapes at high angles of attack (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Water tunnel visualization of the flow about bodies at high angles of attack was done. Wind tunnel tests on a series of models with non-circular cross sections are reported.
    Keywords: AERODYNAMICS
    Type: NASA-CR-169611 , NAS 1.26:169611
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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