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  • AERODYNAMICS  (8)
  • Electronic structure and strongly correlated systems  (2)
  • 2015-2019  (2)
  • 1990-1994  (8)
  • 1
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    Direct observation of anisotropic small-hole polarons in an orthorhombic structure of $\mathrm{BiV}{\mathrm{O}}_{4}$ films (2018)
    American Physical Society (APS)
    Details
    Publication Date: 2018-05-26
    Description: Author(s): A. Chaudhuri, L. Mandal, X. Chi, M. Yang, M. C. Scott, M. Motapothula, X. J. Yu, P. Yang, Y. Shao-Horn, T. Venkatesan, A. T. S. Wee, and A. Rusydi Here, we report an anisotropic small-hole polaron in an orthorhombic structure of BiV O 4 films grown by pulsed-laser deposition on yttrium-doped zirconium oxide substrate. The polaronic state and electronic structure of BiV O 4 films are revealed using a combination of polarization-dependent x-ray abso... [Phys. Rev. B 97, 195150] Published Fri May 25, 2018
    Keywords: Electronic structure and strongly correlated systems
    Print ISSN: 1098-0121
    Electronic ISSN: 1095-3795
    Topics: Physics
    Published by American Physical Society (APS)
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  • 2
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    Transfer of spectral weight across the gap of Sr_{2} IrO_{4} induced by La doping (2015)
    American Physical Society (APS)
    Details
    Publication Date: 2015-09-01
    Description: Author(s): Véronique Brouet, Joseph Mansart, Luca Perfetti, Christian Piovera, Ivana Vobornik, Patrick Le Fèvre, François Bertran, Scott C. Riggs, M. C. Shapiro, Paula Giraldo-Gallo, and Ian R. Fisher We study with angle-resolved photoelectron spectroscopy the evolution of the electronic structure of Sr 2 IrO 4 , when holes or electrons are introduced, through Rh or La substitutions. At low dopings, the added carriers occupy the first available states, at the bottom or top of the gap, revealing an as… [Phys. Rev. B 92, 081117(R)] Published Mon Aug 31, 2015
    Keywords: Electronic structure and strongly correlated systems
    Print ISSN: 1098-0121
    Electronic ISSN: 1095-3795
    Topics: Physics
    Published by American Physical Society (APS)
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  • 3
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    Aeroassist flight experiment heating-rate sensitivity study (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 5; 456-462
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic heating on AFE due to nonequilibrium flow with variable entropy at boundary layer edge (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: A method of predicting the aerobrake aerothermodynamic environment on the NASA Aeroassist Flight Experiment (AFE) vehicle is described. Results of a three dimensional inviscid nonequilibrium solution are used as input to an axisymmetric nonequilibrium boundary layer program to predict AFE convective heating rates. Inviscid flow field properties are obtained from the Euler option of the Viscous Reacting Flow (VRFLO) code at the boundary layer edge. Heating rates on the AFE surface are generated with the Boundary Layer Integral Matrix Procedure (BLIMP) code for a partially catalytic surface composed of Reusable Surface Insulation (RSI) times. The 1864 kg AFE will fly an aerobraking trajectory, simulating return from geosynchronous Earth orbit, with a 75 km perigee and a 10 km/sec entry velocity. Results of this analysis will provide principal investigators and thermal analysts with aeroheating environments to perform experiment and thermal protection system design.
    Keywords: AERODYNAMICS
    Type: ESA, Aerothermodynamics for Space Vehicles; p 371-376
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A static investigation of the thrust vectoring system of the F/A-18 high-alpha research vehicle (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A static (wind-off) test was conducted in the static test facility of the Langley 16-foot Transonic Tunnel to evaluate the vectoring capability and isolated nozzle performance of the proposed thrust vectoring system of the F/A-18 high alpha research vehicle (HARV). The thrust vectoring system consisted of three asymmetrically spaced vanes installed externally on a single test nozzle. Two nozzle configurations were tested: A maximum afterburner-power nozzle and a military-power nozzle. Vane size and vane actuation geometry were investigated, and an extensive matrix of vane deflection angles was tested. The nozzle pressure ratios ranged from two to six. The results indicate that the three vane system can successfully generate multiaxis (pitch and yaw) thrust vectoring. However, large resultant vector angles incurred large thrust losses. Resultant vector angles were always lower than the vane deflection angles. The maximum thrust vectoring angles achieved for the military-power nozzle were larger than the angles achieved for the maximum afterburner-power nozzle.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4359 , L-17002 , NAS 1.15:4359
    Format: application/pdf
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  • 6
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    Static performance of a cruciform nozzle with multiaxis thrust-vectoring and reverse-thrust capabilities (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A multiaxis thrust vectoring nozzle designed to have equal flow turning capability in pitch and yaw was conceived and experimentally tested for internal, static performance. The cruciform-shaped convergent-divergent nozzle turned the flow for thrust vectoring by deflecting the divergent surfaces of the nozzle, called flaps. Methods for eliminating physical interference between pitch and yaw flaps at the larger multiaxis deflection angles was studied. These methods included restricting the pitch flaps from the path of the yaw flaps and shifting the flow path at the throat off the nozzle centerline to permit larger pitch-flap deflections without interfering with the operation of the yaw flaps. Two flap widths were tested at both dry and afterburning settings. Vertical and reverse thrust configurations at dry power were also tested. Comparison with two dimensional convergent-divergent nozzles showed lower but still competitive thrust performance and thrust vectoring capability.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3188 , L-16958 , NAS 1.60:3188
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The personal aircraft: Status and issues (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Paper summarizes the status of personal air transportation with emphasis upon VTOL and converticar capability. The former obviates the need for airport operations for personal aircraft whereas the latter provides both ground and air capability in the same vehicle. Fully automatic operation, ATC and navigation is stressed along with consideration of acoustic, environmental and cost issues.
    Keywords: AERODYNAMICS
    Type: NASA-TM-109174 , NAS 1.15:109174
    Format: application/pdf
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  • 8
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    Two-dimensional converging-diverging rippled nozzles at transonic speeds (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was performed in the Langley 16-Foot Transonic tunnel to determine the effects of external and internal flap rippling on the aerodynamics of a nonaxisymmetric nozzle. Data were obtained at several Mach numbers from static conditions to 1.2 over a range of nozzle pressure ratios. Nozzles with chordal boattail angles of 10, 20, and 30 degrees, with and without surface rippling, were tested. No effect on discharge coefficient due to surface rippling was observed. Internal thrust losses due to surface rippling were measured and attributed to a combination of additional internal skin friction and shock losses. External nozzle drag for the baseline configurations were generally less than that for the rippled configurations at all free-stream Mach numbers tested. The difference between the baseline and rippled nozzle drag levels generally increased with increasing boat tail angle. The thrust-minus-drag level for each rippled nozzle configuration was less than the equivalent baseline configuration for each Mach number at the design nozzle pressure ratio.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3440 , L-17265 , NAS 1.60:3440
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  • 9
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    Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to evaluate the internal performance of a nonaxisymmetric convergent divergent nozzle designed to have simultaneous pitch and yaw thrust vectoring capability. This concept utilized divergent flap deflection for thrust vectoring in the pitch plane and flow-turning deflectors installed within the divergent flaps for yaw thrust vectoring. Modifications consisting of reducing the sidewall length and deflecting the sidewall outboard were investigated as means to increase yaw-vectoring performance. This investigation studied the effects of multiaxis (pitch and yaw) thrust vectoring on nozzle internal performance characteristics. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 13.0. The results indicate that this nozzle concept can successfully generate multiaxis thrust vectoring. Deflection of the divergent flaps produced resultant pitch vector angles that, although dependent on nozzle pressure ratio, were nearly equal to the geometric pitch vector angle. Losses in resultant thrust due to pitch vectoring were small or negligible. The yaw deflectors produced resultant yaw vector angles up to 21 degrees that were controllable by varying yaw deflector rotation. However, yaw deflector rotation resulted in significant losses in thrust ratios and, in some cases, nozzle discharge coefficient. Either of the sidewall modifications generally reduced these losses and increased maximum resultant yaw vector angle. During multiaxis (simultaneous pitch and yaw) thrust vectoring, little or no cross coupling between the thrust vectoring processes was observed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3369 , L-17229 , NAS 1.60:3369
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Internal performance of Highly Integrated Deployable Exhaust Nozzles (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The internal performance characteristics of Highly Integrated Deployable Exhaust Nozzles (HIDEN) applicable to advanced short take-off and vertical landing aircraft have been investigated. Four nozzle concepts, designed for fan and core flow installations, were tested with varying contraction ratio and nozzle exit plane shape. In addition, two offtake duct designs, along with several centerbody and blocker geometries were tested to evaluate their effect on the static thrust and flow performance. This investigation was conducted in the static test facility of the NASA Langley 16-Foot Transonic Tunnel. A six-component strain-gage balance collected force and moment data, and static pressure, total pressure, and total temperature measurements were also made internal to the model. Room temperature, dry high-pressure air was used to simulate jet exhaust. The results indicate that the internal performance of these HIDEN concepts is comparable to previously tested nozzle concepts designed for thrust vectoring about a bearing plane. This report presents the configuration design of the HIDEN concepts and the results of the internal performance testing.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2570 , ; 15 p.|AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States
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