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  • AERODYNAMICS  (9)
  • GEOPHYSICS  (5)
  • ACOUSTICS  (4)
  • Polymer and Materials Science
  • 1985-1989  (20)
  • 1
    Electronic Resource
    Electronic Resource
    Computer graphics display of 3-D analysis data (1986)
    Chichester [u.a.] : Wiley-Blackwell
    Surface and Interface Analysis 8 (1986), S. 139-146 
    Details
    ISSN: 0142-2421
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Physics
    Notes: The development of a computer program to display results of 3-D analysis is described and discussed. The program can data in the desired format, display a representation of a 3-D grid in the recent version limited to 10 × 10 × 10 divisions, and fill the grid with colors and shades representing different chemical elements and their concentration. To allow a detailed inspection of the analyzed volume from different viewing angles, the whole 3-D scene can be rotated to any desired position. To allow inspection of the interior of the analyzed volume, the display can be cross-sectioned or scanned through in various directions. Capabilities and limitations of the program as well as unresolved problems and suggestions for its future development are presented. The program is tested using a model data file representing a simplified 3-D microelectronic circuit and a complex shape inclusion in the matrix material.
    Additional Material: 17 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/sia.740080402
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Investigation of the Combustion of Liquid Gun Propellants in Closed Chambers (1987)
    Weinheim : Wiley-Blackwell
    Propellants, Explosives, Pyrotechnics 12 (1987), S. 133-136 
    Details
    ISSN: 0721-3115
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Closed chamber tests on hydroxylammonium nitrate (HAN) based liquid monopropellants (LPs) were performed at loading densities of about 0.2 g/cm3 at both the Fraunhofer-Institut für Kurzzeitdynamik (EMI-AFB), and the Ballistic Research Laboratory (BRL). The objective of the studies was to investigate the decomposition of the HAN based liquid propellants under various conditions. Pressure and temperatures were measured for both neat and intentionally contaminated monopropellants. Contaminants tested were iron, copper, aluminum, and nickel at concentrations of about 100 ppm. The temperatures were determined using both thermocouples and specially designed temperature (emission) gages. The data illustrate the behavior of the liquid propellants during the decomposition phase.
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/prep.19870120406
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    Paper (German National Licenses)
    Fulltext
  • 3
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    Design of the low-speed NLF(1)-0414F and the high-speed HSNLF(1)-0213 airfoils with high-lift systems (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The design and testing of Natural Laminar Flow (NLF) airfoils is examined. The NLF airfoil was designed for low speed, having a low profile drag at high chord Reynolds numbers. The success of the low speed NLF airfoil sparked interest in a high speed NLF airfoil applied to a single engine business jet with an unswept wing. Work was also conducted on the two dimensional flap design. The airfoil was decambered by removing the aft loading, however, high design Mach numbers are possible by increasing the aft loading and reducing the camber overall on the airfoil. This approach would also allow for flatter acceleration regions which are more stabilizing for cross flow disturbances. Sweep could then be used to increase the design Mach number to a higher value also. There would be some degradation of high lift by decambering the airfoil overall, and this aspect would have to be considered in a final design.
    Keywords: AERODYNAMICS
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 3; p 637-671
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental validation of a two-dimensional shear-flow model for determining acoustic impedance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted to validate a two-dimensional shear-flow analytical model for determining the acoustic impedance of a liner test specimen in a grazing-incidence, grazing-flow environment. The tests were limited to a test specimen chosen to exhibit minimal effects of grazing flow so that the results obtained by using the shear-flow analytical model would be expected to match those obtained from normal-incidence impedance measurements. Impedances for both downstream and upstream sound propagation were generally consistent with those from normal-incidence measurements. However, sensitivity of the grazing-incidence impedance to small measurement or systematic errors in propagation constant varied dramatically over the range of test frequencies.
    Keywords: ACOUSTICS
    Type: NASA-TP-2679 , L-16203 , NAS 1.60:2679
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Study of lee-side flows over conically cambered Delta wings at supersonic speeds, part 2 (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was performed in which surface pressure data, flow visualization data, and force and moment data were obtained on four conical delta wing models which differed in leading edge camber only. Wing leading edge camber was achieved through a deflection of the outboard 30% of the local wing semispan of a reference 75 deg swept flat delta wing. The four wing models have leading edge deflection angles delta sub F of 0, 5, 10, and 15 deg measured streamwise. Data for the wings with delta sub F = 10 and 15 deg showed that hinge line separation dominated the lee-side wing loading and prohibited the development of leading edge separation on the deflected portion of wing leading edge. However, data for the wing with delta sub F = 5 deg showed that at an angle of attack of 5 deg, a vortex was positioned on the deflected leading edge with reattachment at the hinge line. Flow visualization results were presented which detail the influence of Mach number, angle of attack, and camber on the lee-side flow characteristics of conically cambered delta wings. Analysis of photographic data identified the existence of 12 distinctive lee-side flow types.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2660-PT-2 , L-16192 , NAS 1.60:2660-PT-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Study of lee-side flows over conically cambered delta wings at supersonic speeds, part 1 (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was performed in which surface pressure data, flow visualization data, and force and moment data were obtained on four conical delta wing models which differed in leading-edge camber only. Wing leading-edge camber was achieved through a deflection of the outboard 30% of the local wind semispan of a reference 75 degrees swept flat delta wing. The four wing models have leading-edge deflection angles delta sub F of 0, 5, 10, and 15 degrees measured streamwise. Data for the wings with delta sub F = 10 and 15 degrees showed that hinge-line separation dominated the lee-side wing loading and prohibited the develpment of leading-edge separation on the deflected portion of wing leading edge. However, data for the wing with delta sub F = 5 degrees, a vortex was positioned on the deflected leading edge with reattachment at the hinge line. Flow visualization results were presented which detail the influence of Mach number, angle of attack, and camber on the lee-side flow characteristics of conically cambered delta wings. Analysis of photgraphic data identified the existence of 12 distinctive lee-side flow types. In general, the aerodynamic force and moment data correlated well with the pressure and flow visualization data.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2660-PT-1 , L-16192 , NAS 1.60:2660-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A method for determining acoustic-liner admittance in ducts with sheared flow in two-cross-sectional directions (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is developed for determining the acoustic admittance of a test liner installed in the wall of a grazing flow impedance tube. The mean flow is permitted flow gradients in both cross-sectional directions of the tube. The unknown admittance value is obtained by solving an eigenvalue problem. This eigenvalue problem results from the application of the finite-element method to the partial differential equation and boundary conditions governing the acoustic field. The credibility of the method is established by comparing results with exact solutions obtained for a constant mean-flow profile and with previous results for cases involving shear in only one cross-sectional direction. Excellent comparisons are obtained in both cases. The analysis is used in conjunction with a limited amount of experimental data and shows that the flow must be accurately modeled in order to determine the acoustic-liner properties.
    Keywords: ACOUSTICS
    Type: NASA-TP-2518 , L-15997 , NAS 1.60:2518
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Airfoil large-eddy breakup devices for turbulent drag reduction (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Large-eddy breakup devices were tested in a turbulent boundary layer at a momentum thickness Reynolds number of 7400. The drag reducing characteristics of thin, tapered plates, NACA 0009, and NACA 4409 airfoil shapes were determined and compared with lower Reynolds number data obtained with thin elements. The results indicate that at the higher Reynolds numbers of the present tests the thin, tapered plates in a tandem arrangement produced large downstream skin-friction reductions (maximum 0/40 percent/), and gave net drag reductions at least as large as for lower Reynolds numbers. Tandem NACA 0009 airfoils, which were approximately 10 times thicker than the thin plates, gave similar results with a maximum downstream skin-friction reduction of 0(30 percent) and a net drag reduction of 7 percent. The device drag for this shape was determined to be near laminar skin friction. The NACA 4409 airfoils suffered large regions of separated flow and produced no net drag reduction.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0520
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Chemical kinetics and photochemical data for use in stratospheric modeling (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Rate constants and photochemical cross sections are presented. The primary application of the data is for modeling of the stratospheric processes, with particular emphasis on the ozone layer and its possible perturbation by anthropogenic and natural phenomena.
    Keywords: GEOPHYSICS
    Type: NASA-CR-176198 , NAS 1.26:176198 , JPL-PUB-85-37
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A vortex-lattice method for general, unsteady aerodynamics (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A general method of calculating unsteady, incompressible, inviscid, three-dimensional flows around arbitrary planforms has been developed. The method is an extension of the vortex-lattice technique. It is not limited by aspect ratio, camber, or angle of attack, as long as vortex breakdown does not occur above the surface of the wing and separation occurs only along sharp edges. As the wing performs arbitrary maneuvers, the position of the wake and the distribution of circulation on the wing and in the wake are obtained as functions of time. One desirable feature of the present method is its ability to treat steady lifting flows very efficiently. Several examples of steady and unsteady flows are presented. These include rectangular wings, with and without flaps, delta, and cropped delta wings.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 43-49
    Format: text
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