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  • 1
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    Longitudinal vortex control - Techniques and applications (The 32nd Lanchester Lecture) (1992)
    In:  Other Sources
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    Publikationsdatum: 2011-08-24
    Beschreibung: A summary is presented of vortex control applications and current techniques for the control of longitudinal vortices produced by bodies, leading edges, tips and intersections. Vortex control has up till now been performed by many approaches in an empirical fashion, assisted by the essentially inviscid nature of much of longitudinal vortex behavior. Attention is given to Reynolds number sensitivities, vortex breakdown and interactions, vortex control on highly swept wings, and vortex control in juncture flows.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aeronautical Journal (ISSN 0001-9240); 96; 958; p. 293-312.
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  • 2
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    Unsteady two- and three-dimensional Navier-Stokes simulations of multistage turbomachinery flows (1992)
    In:  Other Sources
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    Publikationsdatum: 2011-08-24
    Beschreibung: The flow-field within an axial flow turbomachine, such as a turbine or compressor, is extremely complex because of three-dimensional features such as hub-corner stall, tip-leakage flows, and airfoil wakes. These flow features interact with each other and with rotor and stator airfoils inducing time-varying forces on the airfoils. These complicated rotor-stator interactions must be understood in order to design turbomachines that are light and compact as well as reliable and efficient. Two codes, STAGE-2 and STAGE-3, have been developed to compute these unsteady rotor-stator interaction flows in multistage turbomachines. An implicit, thin-layer Euler/Navier-Stokes zonal algorithm is used to compute the unsteady flow-field within both turbine and compressor configurations. Results include surface pressures and wake profiles for two-dimensional turbine and compressor configurations and surface pressures for a three-dimensional single-stage turbine configuration. The results compare well with experimental data and other unsteady computations.
    Schlagwort(e): AERODYNAMICS
    Materialart: Computing Systems in Engineering (ISSN 0956-0521); 3; 1-4; p. 231-240.
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  • 3
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    Probabilistic structural analysis of adaptive/smart/intelligent space structures (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A three-bay, space, cantilever truss is probabilistically evaluated for adaptive/smart/intelligent behavior. For each behavior, the scatter (ranges) in buckling loads, vibration frequencies, and member axial forces are probabilistically determined. Sensitivities associated with uncertainties in the structure, material and load variables that describe the truss are determined for different probabilities. The relative magnitude for these sensitivities are used to identify significant truss variables that control/classify its behavior to respond as an adaptive/smart/intelligent structure. Results show that the probabilistic buckling loads and vibration frequencies increase for each truss classification, with a substantial increase for intelligent trusses. Similarly, the probabilistic member axial forces reduce for adaptive and intelligent trusses and increase for smart trusses.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Intelligent Material Systems and Structures (ISSN 1045-389X); 3; 4; p. 600-616.
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  • 4
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    Design of highly damage-tolerant sandwich panels (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The effects of different fabrication procedures to increase the damage tolerance of sandwich panels were studied. Baseline panels consisted of a 25.4 mm premolded core, surfaced with 177 C cure film adhesive and carbon-bismaleimide prepreg which were subsequently cocured onto the core. It was found that panels with a prefabricated skin, which was subsequently bonded onto the core with room temperature cure adhesive, showed greatly increased damage tolerance.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International SAMPE Symposium and Exhibition, 37th, Anaheim, CA, Mar. 9-12, 1992, Proceedings (A93-15726 04-23); p. 1228-1242.
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  • 5
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    Numerical simulation of jet noise (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Jet noise and jet-induced structural loads have become key issues in the design of commercial and military aircraft. Computational Fluid Dynamics (CFD) can be of use in predicting the underlying jet shear-layer instabilities and, in conjunction with classical acoustic theory, jet noise. The computational issues involved in the resolution of high Reynolds number unsteady jet flows are addressed in this paper. Once these jet flows can be accurately resolved, it should be possible to use acoustic theory to extract, for example, the far-field jet noise. An assessment of future work and computational resources required for directly computing far-field jet noise is also presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Computing Systems in Engineering (ISSN 0956-0521); 3; 1-4; p. 169-179.
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  • 6
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    Supersonic laminar flow control (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A development status evaluation is presented for the theoretical understanding and design conceptualization of boundary layer control (BLC) systems applicable to supersonic transports, such as the currently envisioned NASA High Speed Civil Transport. By reducing fuel burned, supersonic BLC techniques could expand ranges to Pacific-crossing scales, while lowering sonic boom effects and upper-atmosphere pollution and even reducing skin friction temperature. The critical consideration for supersonic BLC is the presence of wave effects.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 233-245.
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  • 7
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    Wave interaction theory and LFC (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Attention is drawn to the influence of preexisting finite-amplitude instabilities on the growth of other disturbances; current design tools for LFC take no notice of this kind of interaction. When a rational accounting is accomplished for the evolution of incoming disturbances in finite-amplitude solutions of the equations of motion, future transition-prediction methods will need to take these wave interactions into account. Attention is given here to interactions in the presence of crossflow vortices and interactions involving Goertler vortices.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 223-232.
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  • 8
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    Laminar flow control - Introduction and overview (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A development history and a development-trends evaluation are presented for laminar flow controlled airfoil technologies and design concepts, including the search for 'natural' laminar flow and actively controlled flow via suction through small pores on the airfoil surface. While most NASA activities in this field have been concerned with subsonic aircraft, it has been projected that the control of boundary layer turbulence may be even more critical to the aerodynamic efficiency of supersonic aircraft. Developmental programs for these techniques have been conducted with several modified conventional aircraft.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 1-21.
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  • 9
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    Subsonic natural-laminar-flow airfoils (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An account is given of the development history of natural laminar-flow (NLF) airfoil profiles under guidance of an experimentally well-verified theoretical method for the design of airfoils suited to virtually all subcritical applications. This method, the Eppler Airfoil Design and Analysis Program, contains a conformal-mapping method for airfoils having prescribed velocity-distribution characteristics, as well as a panel method for the analysis of potential flow about given airfoils and a boundary-layer method. Several of the NLF airfoils thus obtained are discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 143-176.
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  • 10
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    Buckling of symmetrically laminated plates with compression, shear, and in-plane bending (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 12; p. 2959-2965.
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  • 11
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    Energetics of gas-surface interactions in transitional flows at entry velocities (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 786-793.
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  • 12
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    Shock interference prediction using direct simulation Monte Carlo (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 780-785.
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  • 13
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    On the use of the hole-drilling technique for residual stress measurements in thin plates (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The strain gage blind hole-drilling technique may be used to determine residual stresses at and below the surface of components. In this paper, the hole-drilling analysis methodology for thick plates is reviewed, and experimental data are used to evaluate the methodology and to assess its applicability to thin plates. Data on the effects of gage pattern, surface preparation, hole spacing, hole eccentricity, and stress level are also presented.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: ASME, Transactions, Journal of Solar Energy Engineering (ISSN 0199-6231); p. 292-299.
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  • 14
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    Scaling of energy absorbing composite plates (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The energy absorption response and crushing characteristics of geometrically scaled graphite-Kevlar epoxy composite plates were investigated. Three different trigger mechanisms including chamfer, notch, and steeple geometries were incorporated into the plate specimens to initiate crushing. Sustained crushing was achieved with a simple test fixture which provided lateral support to prevent global buckling. Values of specific sustained crushing stress (SSCS) were obtained which were comparable to values reported for tube specimens from previously published data. Two sizes of hybrid plates were fabricated; a baseline or model plate, and a full-scale plate with in-plane dimensions scaled by a factor of two. The thickness dimension of the full-scale plates was increased using two different techniques; the ply-level method in which each ply orientation in the baseline laminate stacking sequence is doubled, and the sublaminate technique in which the baseline laminate stacking sequence is repeated as a group. Results indicated that the SSCS is independent of trigger mechanism geometry. However, a reduction in the SSCS of 10-25 percent was observed for the full-scale plates as compared with the baseline specimens, indicating a scaling effect in the crushing response.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 2 (A93-35901 14-01); p. 1431-1440.
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  • 15
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    Hover performance analysis of advanced rotor blades (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: This is an effort aimed at validating recent hover prediction methods. The experimental basis for this validation work is an extensive set of loads, wake and performance data, which were obtained from a pressure instrumented model UH-60 rotor tested at the Sikorsky hover test facility and at Duits-Nederlandse Windtunnel (DNW). This model was equipped with replaceable tips - including a tapered and a BERP-type tip - which permitted studies of the effects of rotor geometry. The central prediction method studied is a free-wake, vortex embedded, full-potential CFD method - called HELIX-I. It is found that the HELIX-I code produces very good comparisons with the data including wake, surface pressure and performance. Comparisons with the measured radial load distributions have permitted an improved understanding of the wake resolution modelling requirements of CFD methods. Since HELIX-I is a combined Eulerian/Lagrangian method, limited comparisons are also made with a Lagrangian boundary element code (called EHPIC) and an Eulerian Navier-Stokes code (called TURNS). In most cases all methods produce good comparisons with the data. It is found that the HELIX-I code provides a good compromise between the speed of boundary integral methods and the comprehensive nature of Navier-Stokes methods.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 2 (A93-35901 14-01); p. 1367-1384.
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  • 16
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    Shadowgraph flow visualization of isolated tiltrotor and rotor/wing wakes (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Shadowgraph flow visualization images were acquired from a 0.184-scale tiltrotor and wing in hover. Measurements and details of the vortex core structure were examined as a function of thrust condition and wake age. Experimental data for the isolated rotor wake geometry and rotor wake interactions with a semi-span wing and image plane were acquired. Quantitative measurements and comparisons of wake geometry and distortion were made for three configurations: the isolated rotor, rotor/wing, and rotor/wing/image plane. Comparisons between tiltrotor and helicopter rotor wake geometry measurements were made. Experimental wake geometry data were also compared with two wake models. Suggestions for improvements to existing prescribed-wake and free-wake models are proposed.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 2 (A93-35901 14-01); p. 1323-1344.
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  • 17
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    A study of the rotor wake of a small-scale rotor model in forward flight using laser light sheet flow visualization with comparisons to analytical models (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An experimental investigation was conducted in the 14 by 22 ft subsonic tunnel at NASA Langley Research Center to quantify the rotor wake behind a scale model helicopter rotor in forward flight (mu = 0.15 and 0.23) at one thrust level (C sub T = 0.0064). The rotor system used in the present test consisted of a four-bladed, fully articulated hub and utilized blades of rectangular planform with a NACA-0012 airfoil section. A laser light sheet, seeded with propylene glycol smoke, was used to visualize the flow in planes parallel and perpendicular to the freestream flow. Quantitative measurements of vortex location, vertical skew angle, and vortex particle void radius were obtained for vortices in the flow; convective velocities were obtained for blade tip vortices. Comparisons were made between the experimental results and the wake geometry generated by computational predictions. The results of these comparisons show that the interaction between wake vortex structures is an important consideration for correctly predicting the wake geometry.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 697-719.
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  • 18
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    Numerical simulation of a hovering rotor using embedded grids (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The flow field for a rotor blade in hover was computed by numerically solving the compressible thin-layer Navier-Stokes equations on embedded grids. In this work, three embedded grids were used to discretize the flow field - one for the rotor blade and two to convect the rotor wake. The computations were performed at two hovering test conditions, for a two-bladed rectangular rotor of aspect ratio six. The results compare fairly with experiment and illustrates the use of embedded grids in solving helicopter type flow fields.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 429-445.
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  • 19
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    A finite-volume Euler solver for computing rotary-wing aerodynamics on unstructured meshes (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An unstructured-grid solver for the unsteady Euler equations has been developed for predicting the aerodynamics of helicopter rotor blades. This flow solver is a finite-volume scheme that computes flow quantities at the vertices of the mesh. Special treatments are used for the flux differencing and boundary conditions in order to compute rotary-wing flowfields, and these are detailed in the paper. The unstructured-grid solver permits adaptive grid refinement in order to improve the resolution of flow features such as shocks, rotor wakes and acoustic waves. These capabilities are demonstrated in the paper. Example calculations are presented for two hovering rotors. In both cases, adaptive-grid refinement is used to resolve high gradients near the rotor surface and also to capture the vortical regions in the rotor wake. The computed results show good agreement with experimental results for surface airloads and wake geometry.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 419-428.
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  • 20
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    Control of resonant frequencies in adaptive structures by prestressing (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The natural vibration frequencies of a structure can be affected by inducing stress in the structure. The success of this kind of control of the resonant frequencies of a truss structure depends on the geometry of the structure. It is shown that in adaptive truss structures the method is effective for vibrations in less stiff directions, such as the normal direction of the plane containing all of the bars of a node, suggesting its applicability for cable, membrane, and thin plate and shell structures.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: Joint Japan(U.S. Conference on Adaptive Structures, 2nd, Nagoya, Japan, Nov. 12-14, 1991, Collection of Papers (A93-31226 11-18); p. 297-314.
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  • 21
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    Scale effects in the response and failure of fiber reinforced composite laminates loaded in tension and in flexure (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The feasibility of using scale model testing for predicting the full-scale behavior of flat composite coupons loaded in tension and beam-columns loaded in flexure is examined. Classical laws of similitude are applied to fabricate and test replica model specimens to identify scaling effects in the load response, strength, and mode of failure. Experiments were performed on graphite-epoxy composite specimens having different laminate stacking sequences and a range of scaled sizes. From the experiments it was deduced that the elastic response of scaled composite specimens was independent of size. However, a significant scale effect in strength was observed. In addition, a transition in failure mode was observed among scaled specimens of certain laminate stacking sequences. A Weibull statistical model and a fracture mechanics based model were applied to predict the strength scale effect since standard failure criteria cannot account for the influence of absolute specimen size on strength.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composite Materials (ISSN 0021-9983); 26; 18; p. 2674-2705.
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  • 22
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    Eigenvalue error analysis of viscously damped structures using a Ritz reduction method (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The efficient solution of the eigenvalue problem that results from inserting passive dampers with variable stiffness and damping coefficients into a structure is addressed. Eigenanalysis of reduced models obtained by retaining a number of normal modes augmented with Ritz vectors corresponding to the static solutions resulting from the load patterns introduced by the dampers has been empirically shown to yield excellent approximations to the full eigenvalue problem. An analysis of this technique in the case of a single damper is presented. A priori and a posteriori error estimates are generated and tested on numerical examples. Comparison theorems with modally truncated models and a Markov parameter matching reduced-order model are derived. These theorems corroborate the heuristic that residual flexibility methods improve low-frequency approximation of the system. The analysis leads to other techniques for eigenvalue approximation. Approximate closed-form solutions are derived that include a refinement to eigenvalue derivative methods for approximation. An efficient Newton scheme is also developed. A numerical example is presented demonstrating the effectiveness of each of these methods.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 12; p. 2935-2944.
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  • 23
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    Development of the wake of an airfoil with riblets (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 12; p. 2817, 2818. Abrid
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  • 24
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    Acoustic testing of high-temperature panels (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 6; p. 1130-1136.
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  • 25
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    Environmental effects on long term behavior of composite laminates (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Model equations are presented for approximate methods simulating the long-term behavior of composite materials and structures in hot/humid service environments. These equations allow laminate property upgradings with time, and can account for the effects of service environments on creep response. These methodologies are illustrated for various individual and coupled temperature/moisture, longitudinal/transverse, and composite material type cases. Creep deformation is noted to rise dramatically for cases of matrix-borne, but not of fiber-borne, loading in hot, humid environments; the coupled influence of temperature and moisture is greater than a mere combination of their individual influences.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 (A93-53376 23-23); p. T852-T866.
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  • 26
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    Effect of service environments on adhesively bonded joints in composite structures (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The models employed in the present computational methods for evaluating severe service-environment effects on adhesively bonded joints in composites are based on composite analyses and structural mechanics, encompassing nonlinear environmental degradation. The methods are demonstrated for the case of a butt joint with a single doubler, subjected to the environmental effects as well as static and cyclic loads. The highest joint strength is noted to be required in the case of cyclic loads and hygrothermal service environments; margins of safety for adhesive material stresses decline rapidly in such cases.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 (A93-53376 23-23); p. T536-T550.
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  • 27
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    Design for inadvertent damage in composite laminates (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Simplified predictive methods and models to computationally simulate durability and damage in polymer matrix composite materials/structures are described. The models include (1) progressive fracture, (2) progressively damaged structural behavior, (3) progressive fracture in aggressive environments, (4) stress concentrations, and (5) impact resistance. Several examples are included to illustrate applications of the models and to identify significant parameters and sensitivities. Comparisons with limited experimental data are made.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 (A93-53376 23-23); p. T256-T269.
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    Design for cyclic loading endurance of composites (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The present paper describes the application of the computer code IPACS (Integrated Probabilistic Assessment of Composite Structures) to air craft wing type structures. The code performs a complete probabilistic structural analysis for composites taking into account the uncertainties in geometry, boundary conditions, material properties, laminate lay-ups and loads. Results of the analysis are presented in terms of cumulative distribution functions (CDF) and probability density function (PDF) of life of a wing type composite structure under different hygrothermal environments subjected to random pressure. The sensitivity of fatigue life to a number of critical structural/material variables is also computed from the analysis.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 (A93-53376 23-23); p. T241-T255.
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  • 29
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    Fracture mechanics parameters for small fatigue cracks (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: This paper presents a review of some common small-crack test specimens, the underlying causes of the small-crack effect, and the fracture-mechanics parameters that have been used to correlate or predict their growth behavior. This review concentrates on continuum mechanics concepts and on the nonlinear behavior of small cracks. The paper reviews some stress-intensity factor solutions for small-crack test specimens and develops some simple elastic-plastic J integral and cyclic J integral expressions that include the influence of crack-closure. These parameters were applied to small-crack growth data on two aluminum alloys, and a fatigue life prediction methodology is demonstrated. For these materials, the crack-closure transient from the plastic wake was found to be the major factor in causing the small-crack effect.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: Small-crack test methods (A93-32758 12-39); p. 6-33.
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  • 30
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    Effects of interply damping layers on the dynamic characteristics of composite plates (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 12; p. 2906-2913.
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  • 31
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    Unsteady simulation of viscous flowfield around F-18 aircraft at large incidence (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 6; p. 986-992.
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  • 32
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    An inverse method for the calculation of through-thickness fatigue crack closure behavior (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An inverse technique was used to calculate through-thickness fatigue crack closure behavior. The through-thickness variation in crack opening stress-intensity factor was calculated by considering the variation in the three-dimensional stress-intensity factor, the variation in crack growth rate along the crack front, and a relationship between the crack growth rate and effective stress-intensity factor range (da/dN-Delta-K(eff)). The three-dimensional stress-intensity factor variation was obtained from an elastic finite element analysis of specific crack-front profiles observed experimentally. The variation in crack growth rate along the crack front was obtained experimentally from comparison of observed crack front changes. The da/dN-Delta-K(eff) relationship was estimated from high stress ratio, constant load amplitude, and fatigue crack growth tests. The through-thickness crack opening stress-intensity factor results agreed with crack opening measurements obtained from fatigue striations, near-tip strain gages, and remote strain and displacement gages.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: Fracture mechanics; Proceedings of the 22nd National Symposium, Atlanta, GA, June 26-28, 1990. Vol. 2 (A93-31576 11-39); p. 46-57.
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  • 33
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    Study on vortex flow control of inlet distortion (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Propulsion and Power (ISSN 0748-4658); 8; 6; p. 1266-1272.
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  • 34
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    Post impact compressive behavior of composites (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: In this paper, the post impact compressive behavior of polymeric composites is studied both analytically and experimentally. In the analytical study, a closed-form solution is obtained for postbuckling of composites with a circular delamination. Using this solution, the reduced stiffness of the impact damaged region is calculated and the residual compressive strengths of quasi-isotropic laminates are predicted as a function of damage size. In the experimental study, in-plane displacements near the damaged region are determined by employing a micro moire interferometry technique. The strain concentrations as well as the compression-after-impact strength have been measured and compared with analytical predictions. Good agreement between the predicted results and experimental data was observed.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: ICAS, Congress, 18th, Beijing, China, Sept. 20-25, 1992, Proceedings. Vol. 2 (A93-14151 03-01); p. 1249-1257.
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  • 35
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    A mechanism responsible for reducing compression strength of through-the-thickness reinforced composite material (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A study was conducted to identify one of the mechanisms that contributes to the reduced compression strength of composite materials with through-the-thickness (TTT) reinforcements. In this study a series of thick (0/90) laminates with stitched and integrally woven TTT reinforcements were fabricated and statically tested. In both the stitching and weaving process a surface loop of TTT reinforcement yarn is created between successive TTT penetrations. It was shown that the surface loop of the TTT reinforcement 'kinked' the in-plane fibers in such a manner that they were made ineffective in carrying compressive load. The improvement in strength by removal of the surface loop and 'kinked' in-plane fibers was between 7 and 35 percent.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composite Materials (ISSN 0021-9983); 26; 12, 1
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  • 36
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    Navier-Stokes simulation of a close-coupled canard-wing-body configuration (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 830-838
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  • 37
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    Aeroelastic effects of spoiler surfaces on a low-aspect-ratio rectangular wing (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 768-773
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  • 38
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    Assessment of compressibility corrections to the k-epsilon model in high-speed shear layers (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 10, O; 2369
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  • 39
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    Combined bending and thermal fatigue of high-temperature metal-matrix composites - Computational simulation (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The nonlinear behavior of a high-temperature metal-matrix composite (HT-MMC) was simulated by using the metal matrix composite analyzer (METCAN) computer code. The simulation started with the fabrication process, proceeded to thermomechanical cyclic loading, and ended with the application of a monotonic load. Classical laminate theory and composite micromechanics and macromechanics are used in METCAN, along with a multifactor interaction model for the constituents behavior. The simulation of the stress-strain behavior from the macromechanical and the micromechanical points of view, as well as the initiation and final failure of the constituents and the plies in the composite, were examined in detail. It was shown that, when the fibers and the matrix were perfectly bonded, the fracture started in the matrix and then propagated with increasing load to the fibers. After the fibers fractured, the composite lost its capacity to carry additional load and fractured.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: International Journal of Damage Mechanics (ISSN 1056-7895); 1; 3, Ju; 290-319
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  • 40
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    Impact damage and residual tension strength of a thick graphite/epoxy rocket motor case (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Impacters of various masses were dropped from various heights onto thick graphite/epoxy filament-wound cylinders. The cylinders represented filament-wound cases made for the booster motors of the Space Shuttle. Tups of various shapes were affixed to the impacters. Some of the cylinders were filled with inert propellant, and some were empty. The cylinders were impacted numerous times around the circumference and then cut into tension coupons, each containing an impact site. The size of the damage and the residual tension strength were measured. For hemispherical tups, strength was reduced as much as 30 percent by nonvisible damage. The damage consisted of matrix cracking and broken fibers. Analytical methods were used to predict the damage and residual tension strength. A factor of safety to account for nonvisible damage was determined. For corner and rod shaped tups, any damage that resulted in strength loss was readily visible.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 3, Ma
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  • 41
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    Plasmadynamic effects in thermochemical nonequilibrium aerobrake flows (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 3, Ma; 319-326
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  • 42
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    Computation of saddle point of attachment (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1561-156
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  • 43
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    On development of a finite dynamic element and solution of associated eigenproblem by a block Lanczos procedure (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The paper first presents the details of the development of a new six-noded plane triangular finite dynamic element. A block Lanczos algorithm is developed next for the accurate and efficient solution of the quadratic matrix eigenvalue problem associated with the finite dynamic element formulation. The resulting computer program fully exploits matrix sparsity inherent in such a discretization and proves to be most efficient for the extraction of the usually required first few roots and vectors, including repeated ones. Most importantly, the present eigenproblem solution is shown to be comparable to that of the corresponding finite element analysis, thereby rendering the associated dynamic element method rather attractive owing to superior convergence characteristics of such elements, presented herein.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 33; 8, Ju
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  • 44
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    Transonic Navier-Stokes computations for an oscillating wing using zonal grids (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 3, Ma; 326-335
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  • 45
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    Tangential, semisubmerged, and internal store carriage and separation (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Accounts are presented of tangential, semisubmerged, and internal store carriage drag, as well as of the results to date of stores-separation investigations employing both computational and experimental methods. It is demonstrated that CFD can contribute to the data base needed for internal stores carriage design and trade studies. Attention is given to the case of an internally carried store separating from its bay at supersonic speeds, where various kinds of interference are encountered. A code is developed for the simulation of these unsteady flows through time-accurate computations; computation results are noted to closely reproduce experiment data.
    Schlagwort(e): AERODYNAMICS
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  • 46
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    Bodies with noncircular cross sections and bank-to-turn missiles (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A development status evaluation is presented for the aerodynamics of missile configurations with noncircular cross-sections and bank-to-turn maneuvering systems, giving attention to cases with elliptical and square cross-sections, as well as bodies with variable cross-sections. The assessment of bank-to-turn missile performance notes inherent stability/control problems. A summary and index are provided for aerodynamic data on monoplanar configurations, including those which incorporate airbreathing propulsion systems.
    Schlagwort(e): AERODYNAMICS
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  • 47
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    Low aspect ratio wings at high angles of attack (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A survey is conducted of the results of investigations into the flowfields and aerodynamic forces associated with low aspect ratio wings at high angles of attack. Attention is given to criteria for the cataloging of these flowfields, the phenomenon of vortex breakdown, with varying wing incidence and Mach number, and the effects of aspect ratio and compressibility. The planforms treated are of rectangular, clipped-delta, and strake-wing combination geometries. Extensive graphic representations of performance trends with varying parameters are furnished.
    Schlagwort(e): AERODYNAMICS
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  • 48
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    A coupled solution method for predicting the thermostructural response of decomposing, expanding polymeric composites (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A new solution method has recently been developed to analyze the thermal and structural response of polymeric composites during chemical decomposition (Sullivan and Salamon, 1992a). This method couples the equations of energy, mass transport and momentum and solves these equations simultaneously at each time step. In this paper, the couples solution method is applied to analyze the response of a glass phenolic composite during its chemical decomposition. The numerical solution to this particular problem was originally performed by Henderson, et al. (1985) and the actual response was measured by Henderson and Hagen (1985) and Ramamurthy (1988). In addition to further verification of the coupled solution method, the present solution offers additional insight into certain physical events which occur during chemical decomposition.
    Schlagwort(e): STRUCTURAL MECHANICS
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    On the placement of active members in adaptive truss structures for vibration control (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The problem of optimal placement of active members which are used for vibration control in adaptive truss structures is investigated. The control scheme is based on the method of eigenvalue assignment as a means of shaping the transient response of the controlled adaptive structures, and the minimization of required control action is considered as the optimization criterion. To this end, a performance index which measures the control strokes of active members is formulated in an efficient way. In order to reduce the computation burden, particularly for the case where the locations of active members have to be selected from a large set of available sites, several heuristic searching schemes are proposed for obtaining the near-optimal locations. The proposed schemes significantly reduce the computational complexity of placing multiple active members to the order of that when a single active member is placed.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Smart Materials and Structures (ISSN 0964-1726); 1; 1, Ma
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  • 50
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    Redesign of the mixed-mode bending delamination test to reduce nonlinear effects (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The mixed-mode bending (MMB) test uses a lever to apply simultaneously mode I and mode II loading to a split-beam specimen. An iterative analysis that accounts for the geometric nonlinearity of the MMB test was developed. The analysis accurately predicted the measured load-displacement response and the strain energy release rate, G, of an MMB test specimen made of AS4/PEEK. The errors in G when calculated using linear theory were found to be as large as 30 percent in some cases. Because it would be inconvenient to use a nonlinear analysis to analyze MMB data, the MMB apparatus was redesigned to minimize the nonlinearity. With the improved apparatus, loads are applied just above the midplane of the test specimen through a roller attached to the lever. This apparatus was demonstrated by measuring the mixed-mode delamination fracture toughhess of the test specimen. The nonlinearity errors associated with testing this tough composite material were less than +/- 3 percent. The data from the improved MMB apparatus analyzed with a linear analysis were similar to those found with the original apparatus and the nonlinear analysis.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composites Technology & Research (ISSN 0885-6804); 14; 1, Sp
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    Numerical study of the effects of reverse sweep on scramjet inlet performance (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Propulsion and Power (ISSN 0748-4658); 8; 3, Ma; 714-719
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  • 52
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    Evaluation of a finite volume method for compressible shear layers (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 5, Ma; 1214-121
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    Mixed-mode fracture in unidirectional graphite epoxy composite laminates with central notch (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Mixed-mode matrix fracture in central notched off-axis unidirectional composite laminates was investigated. A limited number of unidirectional tensile type specimens with a central, horizontal, notch were tested. Crack initiation and propagation were examined under various local stress fields that were controlled by fiber orientations. The tested specimens were simulated using a two dimensional finite element method with constant strain loading. The strain energy release rates along the crack were evaluated via crack closure technique. The variation of critical strain energy rates with off-axis angle was studied. The results from single (one-sided) and double (two-sided) crack simulations were presented and compared.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Reinforced Plastics and Composites (ISSN 0731-6844); 11; 324-338
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  • 54
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    Application of the LAURA code for slender-vehicle aerothermodynamics (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 16-23
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  • 55
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    Implicit Navier-Stokes solver for three-dimensional compressible flows (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 11; p. 2653-2659.
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    Comparison of algebraic turbulence models for afterbody flows with jet exhaust (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Three-dimensional Navier-Stokes simulations have been done for transonic and low supersonic flow past a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes. The jet exhaust is included in the calculations. The investigation compares the performance of the unmodified Baldwin-Lomax turbulence model with its performance when enhanced by the Degani-Schiff and the Goldberg modifications. Solutions are presented for Mach numbers of 0.80, 0.94, and 1.20 at 0-deg angle of attack and a Reynolds number of 20 x 10 to the 6th. The numerical results, which are compared to the wind-tunnel data, show that the three turbulence models predict considerably different shock locations, separated-flow regions, and flowfields.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 11; p. 2716-2722.
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  • 57
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    Mixed mode stress intensity-factors in transversely loaded plates (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An attempt is made to establish the validity of the antiplane solution and to calculate all components of the stress intensity factor (SIF) at the crack front for thin plates subjected to mode III loading. The stress analysis was performed for a range of thickness to crack length (b/a) ratio, which covered long cracks in a thin aircraft fuselage structure (b/a = 0.05).
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: International Journal of Fracture (ISSN 0376-9429); 57; 2; p. R19-R25.
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    Crushing characteristics of composite tubes with 'near-elliptical' cross sections (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: An experimental investigation was conducted to determine whether the energy-absorption capability of near-elliptical cross-section composite tubular specimens is a function of included angle. Each half of the near-elliptical cross-section tube is a segment of a circle. The included angle is the angle created by radial lines extending from the center of the circular segment to the ends of the circular segment. Graphite- and Kevlar-reinforced epoxy material was used to fabricate specimens. Tube internal diameters were 2.54, 3.81, and 7.62 cm, and included angles were 180, 160, 135, and 90 degrees. Based upon the test results from these tubes, energy-absorption capability increased between 10 and 30 percent as included angle decreased between 180 and 90 degrees for the materials evaluated. Energy-absorption capability was a decreasing nonlinear function of the ratio of tube internal diameter to wall thickness.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composite Materials (ISSN 0021-9983); 26; 12, 1
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    Computation of antenna vibration mode elastic-rigid and effective-weight coefficients (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A significant amount of both qualitative and quantitative information about structures can be derived from the elastic-rigid structural coupling matrices, and from the effective modal inertias and masses. Typical finite-element analysis programs do not provide this information as part of the regular output. This report presents an easy way to develop the necessary information from ordinary program output, and shows how to deal with alternative origins for the reference coordinate system.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: IEEE Antennas and Propagation Magazine (ISSN 1045-9243); 34; 3, Ju
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    Application of an unsteady Navier-Stokes solver to transonic turbine design (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Propulsion and Power (ISSN 0748-4658); 8; 5, Se; 1079-108
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    Likelihood estimation for distributed parameter models of large beam-like structures (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A maximum likelihood estimation for distributed parameter models of large flexible structures was formulated. Distributed parameter models involve far fewer unknown parameters than independent modal characteristics or finite element models. The closed form solutions for the partial differential equations with corresponding boundary conditions were derived. The closed-form expressions of sensitivity functions led to highly efficient algorithms for analyzing ground or on-orbit test results. For an illustration of this approach, experimental data of the NASA Mini-Mast truss was used. The estimations of modal properties involve lateral bending modes and torsional modes. The results show that distributed parameter models are promising in the parameter estimation of large flexible structures.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Sound and Vibration (ISSN 0022-460X); 155; 3, Ju; 467-480
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  • 62
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    Applications of artificial neural nets in structural mechanics (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A brief introduction to the fundamental of Neural Nets is given, followed by two applications in structural optimization. In the first case, the feasibility of simulating with neural nets the many structural analyses performed during optimization iterations was studied. In the second case, the concept of using neural nets to capture design expertise was studied.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Structural Optimization (ISSN 0934-4373); 4; 2, Ju; 90-98
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    Gortler instability and supersonic quiet nozzle design (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 8, Au; 2093
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    Predicted pressure distribution on a prop-fan blade through Euler analysis (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 627-631
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  • 65
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    Navier-Stokes computations on swept-tapered wings, including flexibility (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 588-597
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    Navier-Stokes predictions for the F-18 wing and fuselage at large incidence (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 565-574
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  • 67
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    Aerothermodynamics of a 1.6-meter-diameter sphere in hypersonic rarefied flow (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 7, Ju; 1789-179
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  • 68
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    Domain-decomposition algorithm applied to multielement airfoil grids (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1457-146
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    Effect of acoustic excitation on stalled flows over an airfoil (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1492-149
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  • 70
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    Two- and three-dimensional grid generation by an algebraic homotopy procedure (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 5, Ma; 1433
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  • 71
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    Generation and comparison of globally isotropic space-filling truss structures (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The purposes of this paper are to present a rationale for obtaining space-filling truss structures that behave like a globally isotropic continuum and to use continuum modeling to investigate their relative structural efficiencies (e.g., modulus-to-density, strength-to-density, and part-count-to-volume ratios). The trusses considered herein are generated by replication of a characteristic truss cell uniformly through space. The characteristic cells are categorized by one of a set of possible geometric symmetry groups derived using the techniques of crystallography. The implied elastic symmetry associated with each geometric symmetry group is identified to simplify the task of determining stiffness tailoring rules for guaranteeing global isotropy. Four truss geometries are analyzed to determine stiffness tailoring necessary for isotropy. All geometries exhibit equivalent isotropic Poisson's ratios of 1/4 and equivalent modulus-to-density ratios of 1/6 times the modulus-to-density ratio of the material used in their members. The truss configuration that has the lowest percent difference in member lengths is shown to have the lowest component part-count-to-volume ratios of all geometries considered when compared on a basis of equal stiffness, equal strength, and equal mass.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 5, Ma
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  • 72
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    Free vibrations of delaminated beams (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 5, Ma; 1361-137
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  • 73
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    Spectral analysis of wave motion in plane solids with boundaries (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A spectral formulation is employed whereby in-plane stress waves are synthesized from the superposition of components at discrete frequencies and wavenumbers. The summations are performed using the fast Fourier transform and the Fourier series, respectively. Because the components are discrete, the solution to problems (over the entire field) with completely arbitrary loading, both in time and space, is made tractable. Waves generated from a line load acting on an infinite and semiinfinite plane are first considered. A cascade approach is then adopted for the treatment of these waves incident on a free, fixed, and elastic boundary. At each stage, the results are compared with those obtained from the available classical solutions and/or finite element results. These studies will form the basis for the investigation of in-plane stress waves in multiply layered media.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: ASME, Transactions, Journal of Vibration and Acoustics (ISSN 0739-3717); 114; 2, Ap
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    Navier-Stokes solution of transonic cascade flows using nonperiodic C-type grids (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A new kind of C-type grid is proposed, this grid is non-periodic on the wake and allows minimum skewness for cascades with high turning and large camber. Reynolds-averaged Navier-Stokes equations are solved on this type of grid using a finite volume discretization and a full multigrid method which uses Runge-Kutta stepping as the driving scheme. The Baldwin-Lomax eddy-viscosity model is used for turbulence closure. A detailed numerical study is proposed for a highly loaded transonic blade. A grid independence analysis is presented in terms of pressure distribution, exit flow angles, and loss coefficient. Comparison with experiments clearly demonstrates the capability of the proposed procedure.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Propulsion and Power (ISSN 0748-4658); 8; 410-417
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    Navier-Stokes simulation of flow through a highly contoured subsonic diffuser (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The flow through a highly offset subsonic diffuser with cross-sectional profiles that varied from rectangular at the duct entrance to circular at the engine face was numerically simulated. A multizonal approach combined with a two-grid topology was used to represent both the internal and external flowfields, and an implicit, approximately-factored, partially flux-split finite-difference algorithm was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computed static pressures along the inlet wall and total pressures on the engine face were compared with experimental data. In addition, the overall flowfield within the duct was examined in detail. Good agreement is shown between experiment and computations, with the limiting factor being the lack of a reliable turbulence model for internal flow problems.
    Schlagwort(e): AERODYNAMICS
    Materialart: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 34; 473-483
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  • 76
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    Enthalpy damping for high Mach number Euler solutions (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 300
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  • 77
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    Stress versus temperature dependence of activation energies for creep (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The activation energy for creep at low stresses and elevated temperatures is associated with lattice diffusion, where the rate controlling mechanism for deformation is dislocation climb. At higher stresses and intermediate temperatures, the rate controlling mechanism changes from dislocation climb to obstacle-controlled dislocation glide. Along with this change in deformation mechanism occurs a change in the activation energy. When the rate controlling mechanism for deformation is obstacle-controlled dislocation glide, it is shown that a temperature-dependent Gibbs free energy does better than a stress-dependent Gibbs free energy in correlating steady-state creep data for both copper and LiF-22mol percent CaF2 hypereutectic salt.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: ASME, Transactions, Journal of Engineering Materials and Technology (ISSN 0094-4289); 114; 46-50
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  • 78
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    Flow over an all-body hypersonic aircraft - Experiment and computation (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 7-15
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    The new challenge of computational aeroscience (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: This paper discusses NASA's Computational Aerosciences (CAS) Project of the High Performance Computing and Communications Program (HPCCP). The project is aimed at developing advanced, multidisciplinary simulation capabilities for aerospace vehicle and propulsion system design. It is also aimed at overcoming computational performance barriers by accelerating the development of parallel computer technology. The goals and approach of the CAS Project are described and the challenges to its implementation are addressed. Specific vehicle class simulations to be demonstrated and the principal mutidisciplinary modeling approaches to be emphasized are described. The computational speed and memory requirements for representative multidisciplinary applications are estimated. Finally, the state of parallel computer technology including programming issues and the results of performance measurements are explored.
    Schlagwort(e): AERODYNAMICS
    Materialart: In: ICAS, Congress, 18th, Beijing, China, Sept. 20-25, 1992, Proceedings. Vol. 1 (A93-14151 03-01); p. 83-96.
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    Application of computational fluid dynamics to sonic boom near- and mid-field prediction (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 920-926
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  • 81
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    Two-fence concept for efficient trapping of vortices on airfoils (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Previous work on the use of a vortex trapped above a wing in order to produce high lift at low angles of attack is extended here. It is first postulated that the optimum way to trap a vortex is to design the airfoil section and wing so that the flow along the vortex core is minimized. It is then shown that a vertical fence both in front of and behind the separation bubble generated by the trapped vortex is an effective way to reduce the mass flow removal and its associated drag to a negligible amount. In order to show that vertical surfaces upstream and downstream of the vortex separation bubble have an opposite effect on the source requirements for vortex trapping, conformal mapping methods are used to obtain the solutions for a variety of simple two-dimensional, inviscid, incompressible flow configurations. Trapped-vortex flowfield solutions for the flow over flat plate and Clark-Y airfoils are then used to demonstrate that the heights of the fences can be tailored to make the required mass withdrawal (and therefore, the drag due to trapping) to be vanishingly small.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se
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  • 82
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    Euler/experiment correlation of a generic fighter (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 839-846
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  • 83
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    Unsteady shock-vortex interaction on a flexible delta wing (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 790-798
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    Structures that adapt to space (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: It is shown that by allowing adjustments in space, designs that incorporate adaptive structures can reduce initial precision requirements and lower costs. Present and future spacecraft structures will need enhancements in performance, reliability, testability, and cost-effectiveness; unless a structural system meets these demands, it probably will never be implemented operationally. Attention is given to the ASTREX test facility at Edwards AFB that includes embedded piezoelectric, in-line piezoelectric actuator, and magnetostrictive active members whose testbed rapidly slews the spacecraft through large angles and then points it quickly and accurately.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Aerospace America (ISSN 0740-722X); 30; 9, Se
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    Application of a parallel direct simulation Monte Carlo method to hypersonic rarefied flows (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 10, O; 2447-245
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    Crossflow vortex and transition measurements by use of multielement hot films (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 9, Se; 2212-221
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  • 87
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    Modern developments in shear flow control with swirl (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1482
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    Hypersonic shock-wave turbulent-boundary-layer interaction flows (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1480
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    Nonadiabatic and three-dimensional effects in compressible turbulent boundary layers (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 897-904
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    Calculation of real-gas effects on blunt-body trim angles (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 999-1007
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    Two- and three-dimensional effects in the supersonic mixing layer (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 973-981
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  • 92
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    Thermal-structural finite element analysis using linear flux formulation (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 6; 341-348
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    Computational study of incipient leading-edge separation on a supersonic delta wing (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 203-209
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    Evaluation of a Navier-Stokes prediction of a jet in a crossflow (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 185-193
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    Axial compression corner flow with shock impingement (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 288
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    Prediction of the energy-absorption capability of composite tubes (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: A method of predicting the crack-related energy-absorption capability of composite tubes is presented. The method is based upon a phenomenological model of the crushing process exhibited by continuous-fiber-reinforced tubes. A finite element method is used to model the crushing process. The analysis is compared with experiments on Kevlar-epoxy and graphite-epoxy tubes. Reasonable agreement is obtained between the analysis and experiment.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composite Materials (ISSN 0021-9983); 26; 3, 19
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    High-performance equation solvers and their impact on finite element analysis (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: The role of equation solvers in modern structural analysis software is described. Direct and iterative equation solvers which exploit vectorization on modern high-performance computer systems are described and compared. The direct solvers are two Cholesky factorization methods. The first method utilizes a novel variable-band data storage format to achieve very high computation rates and the second method uses a sparse data storage format designed to reduce the number od operations. The iterative solvers are preconditioned conjugate gradient methods. Two different preconditioners are included; the first uses a diagonal matrix storage scheme to achieve high computation rates and the second requires a sparse data storage scheme and converges to the solution in fewer iterations that the first. The impact of using all of the equation solvers in a common structural analysis software system is demonstrated by solving several representative structural analysis problems.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 33; 855-868
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    Correction of sideslip-induced static pressure errors in flight-test measurements (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 114-117
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    Comparison of two Navier-Stokes codes for attached transonic wing flows (1992)
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    Publikationsdatum: 2011-08-24
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Aircraft (ISSN 0021-8669); 29; 101-107
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    Hybrid analysis of deformation using interferometric measurements (1992)
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    Publikationsdatum: 2011-08-24
    Beschreibung: Two hybrid methods of deformation analysis combining moire interferometry and finite element techniques are introduced. The hybrid methods are applied to determine the strain fields in the test section of a composite cruciform specimen in order to evaluate the uniformity of the shear strain field. Both methods show that there are significant shear strain gradients in the specimen test section. One of the hybrid methods - the full-field analysis using the random-node mesh generator - detects the presence of material property nonuniformity which is assumed uniform in the boundary-node method.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: In: International Congress on Experimental Mechanics, 7th, Las Vegas, NV, June 8-11, 1992, Proceedings. Vol. 1 (A94-12901 02-39); p. 111-119.
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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