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  • Analytical Chemistry and Spectroscopy  (3,734)
  • Chemical Engineering  (1,809)
  • AERODYNAMICS  (1,726)
  • 1990-1994  (5,600)
  • 1980-1984  (1,669)
  • 1925-1929
  • 1992  (2,829)
  • 1991  (2,771)
  • 1980  (1,669)
Collection
Keywords
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  • 1990-1994  (5,600)
  • 1980-1984  (1,669)
  • 1925-1929
Year
  • 1
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    Longitudinal vortex control - Techniques and applications (The 32nd Lanchester Lecture) (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: 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)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Computing Systems in Engineering (ISSN 0956-0521); 3; 1-4; p. 231-240.
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  • 3
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    Numerical simulation of jet noise (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Computing Systems in Engineering (ISSN 0956-0521); 3; 1-4; p. 169-179.
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  • 4
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    The hypersonic double ellipse in rarefied flow (1991)
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    Publication Date: 2011-08-24
    Description: The problem of the hypersonic double ellipse in rarefied flow is treated by a particle method using the collision model first described by McDonald (1988). In the approach used here, the computational overhead is reduced by using simple cubic cells. The problem of the definition of complex geometries is addressed by developing an algorithm to define the relation of a body surface to the network of cells.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 2 (A93-42576 17-02); p. 912-923.
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  • 5
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    Application of program LAURA to thermochemical nonequilibrium flow through a nozzle (1991)
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    Publication Date: 2011-08-24
    Description: Program LAURA (Langley Aerothermodynamic Upwind Relaxation Algorithm) is an upwind-biased, point-implicit relaxation algorithm for obtaining the numerical solution to the governing equations for 3D viscous hypersonic flows in chemical and thermal nonequilibrium. The algorithm is derived using a finite-volume formulation in which the inviscid components of flux across cell walls are described with a modified Roe's averaging and with second-order corrections based on Yee's Symmetric Total Variation Diminishing scheme. The code has been applied to Problem 8.2 of this workshop for the case of thermochemical nonequilibrium flow through a nozzle. Chemical reaction rates are defined with the model of Park (1987). Thermal nonequilibrium is modeled using a two-temperature approximation in which the vibrational energies of all molecules are assumed to be in equilibrium at a single temperature which is generally different from the translational-rotational temperature. Two grids were used to define the flow for the original problem, with a stagnation temperature of 6500 K. A third case with a stagnation temperature of 10,000 K is also presented. The solution domain includes the converging nozzle, subsonic flow domain in which the gas is substantially in thermochemical equilibrium and the diverging nozzle, hypersonic flow domain in which the gas is substantially in thermochemical nonequilibrium.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 2 (A93-42576 17-02); p. 1145-1158.
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  • 6
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    Hypersonic cone flow predictions using an implicit upwind space-marching code (1991)
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    Publication Date: 2011-08-24
    Description: Solutions have been computed and results are presented for Problem 1, the case of Mach 9 transitional flow past a 7 deg half-angle cone at zero incidence. The solutions were computed using a code developed for the integration of the parabolized Navier-Stokes equations. The algorithm employed in the code is based on a Roe-type flux-difference-splitting scheme applied following a finite-volume approach. The basic algorithm has been modified to make it implicit and second-order accurate in the crossflow directions. Results are presented in terms of surface pressure and heat transfer as well as boundary layer profiles of pitot pressure, Mach number, and tangential velocity. The case was recalculated several times in an effort to determine sensitivities to such parameters as grid density, wall temperature, turbulence model parameters, as well as freestream expansion. Comparisons with the experimental data are presented and discussed.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 2 (A93-42576 17-02); p. 75-91.
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  • 7
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    Supersonic laminar flow control (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 233-245.
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  • 8
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    Wave interaction theory and LFC (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 223-232.
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  • 9
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    Laminar flow control - Introduction and overview (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 1-21.
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  • 10
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    Subsonic natural-laminar-flow airfoils (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 143-176.
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  • 11
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    Correlation of airloads on a two-bladed helicopter rotor (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Airloads measured on a two-bladed helicopter rotor in flight, from the Tip Aerodynamic and Acoustic Test, are compared with calculations from a comprehensive helicopter analysis (CAMRAD/JA), and the pressures compared with calculations from a full-potential rotor code (FPR). The flight test results cover an advance ratio range from 0.19 to 0.38. The lowest speed case is characterized by the presence of significant blade-vortex interactions. Good correlation of peak-to-peak vortex-induced loads and the corresponding pressures is obtained. The results of the correlation for this two-bladed rotor are substantially similar to the results for three- and four-bladed rotors, concerning the tip vortex core size for best correlation, calculation of the peak-to-peak loads on the retreating side, and calculation of vortex-induced loads on inboard radial stations.
    Keywords: AERODYNAMICS
    Type: In: AHS and Royal Aeronautical Society, Technical Specialists' Meeting on Rotorcraft Acoustics(Fluid Dynamics, Philadelphia, PA, Oct. 15-17, 1991, Proceedings (A93-29401 10-71); 38 p.
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  • 12
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    The development of a CFD potential method for the analysis of tilt-rotors (1991)
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    Publication Date: 2011-08-24
    Description: A new CFD potential code, FPX (eXtended Full-Potential), has been developed for application to both helicopters and tilt-rotors. The code solves the unsteady, three-dimensional full potential equation and is an extension of the rotor code, FPR. Both entropy and viscosity corrections are included to enhance the physical modeling capabilities. A number of efficiency related modifications have yielded a factor of two speed-up in the code. An axial flow capability has been added to treat tilt-rotor in forward flight (cruise mode). In order to employ streamwise periodicity and accurately solve for the propagation of acoustic signals in the tip region, an H-H topology has been added to the basic O-H grid system. Computations are performed for the XV-15 Standard and ATB blades at high-speed conditions. Comparisons are made for the blade aerodynamics and the induced fuselage cabin pressure for a range of Mach numbers. Grid generation, wake treatment, and far-field wall treatment are identified as problem areas with recommendations for future research.
    Keywords: AERODYNAMICS
    Type: In: AHS and Royal Aeronautical Society, Technical Specialists' Meeting on Rotorcraft Acoustics(Fluid Dynamics, Philadelphia, PA, Oct. 15-17, 1991, Proceedings (A93-29401 10-71); 15 p.
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  • 13
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    Recent developments in rotor wake modeling for helicopter noise prediction (1991)
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    Publication Date: 2011-08-24
    Description: A preliminary test/theory correlation evaluation is conducted for wake measurement test results obtained by LDV for a B360 helicopter rotor, at conditions critical to the understanding of wake-rollup and blade-vortex interaction phenomena. The LDV data were complemented by acoustic, blade pressure, rotor performance, and blade/control load measurements.
    Keywords: AERODYNAMICS
    Type: In: AHS and Royal Aeronautical Society, Technical Specialists' Meeting on Rotorcraft Acoustics(Fluid Dynamics, Philadelphia, PA, Oct. 15-17, 1991, Proceedings (A93-29401 10-71); 16 p.
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  • 14
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    Grid-refinement study of hypersonic laminar flow over a 2-D ramp (1991)
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    Publication Date: 2011-08-24
    Description: Computations were made for those test cases of Problem 3 which were designated as laminar flows, viz., test cases 3.1, 3.2, 3.4, and 3.5. These test cases corresponded to flows over a flat plate and a compression ramp at high Mach number and at high Reynolds number. The computations over the compression ramps indicate a substantial streamwise extent of separation. Based on previous experience with separated laminar flows at high Mach numbers which indicated a substantial effect with spatial grid refinement, a series of computations with different grid sizes were performed. Also, for the flat plate, comparisons of the results for two different algorithms were made.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 2 (A93-42576 17-02); p. 244-254.
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  • 15
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    Computational fluid dynamics for hypersonic airbreathing aircraft (1991)
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    Publication Date: 2011-08-24
    Description: A development status evaluation is presented for CFD methods applicable to fuselage-integrated scramjet powerplant incorporating hypersonic vehicles; these methods are critically important due to the unavailability of experimental facilities for such elevated Mach number/high-enthalphy conditions. Advancements are required in algorithm robustness and speed, geometric flexibility, and the inclusion of more complete flow physics. The most serious deficiencies lie in turbulence modeling, the lack of complete transition-prediction methods, and combustion modeling.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 1 (A93-42576 17-02); p. 55-71.
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  • 16
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    CFD for hypersonic propulsion (1991)
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    Publication Date: 2011-08-24
    Description: An overview is given of research activity on the application of computational fluid dynamics (CDF) for hypersonic propulsion systems. After the initial consideration of the highly integrated nature of air-breathing hypersonic engines and airframe, attention is directed toward computations carried out for the components of the engine. A generic inlet configuration is considered in order to demonstrate the highly three dimensional viscous flow behavior occurring within rectangular inlets. Reacting flow computations for simple jet injection as well as for more complex combustion chambers are then discussed in order to show the capability of viscous finite rate chemical reaction computer simulations. Finally, the nozzle flow fields are demonstrated, showing the existence of complex shear layers and shock structure in the exhaust plume. The general issues associated with code validation as well as the specific issue associated with the use of CFD for design are discussed. A prognosis for the success of CFD in the design of future propulsion systems is offered.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 1 (A93-42576 17-02); p. 170-186.
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  • 17
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    Energetics of gas-surface interactions in transitional flows at entry velocities (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 786-793.
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  • 18
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    Shock interference prediction using direct simulation Monte Carlo (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 780-785.
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  • 19
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    Hover performance analysis of advanced rotor blades (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 2 (A93-35901 14-01); p. 1367-1384.
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  • 20
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    Shadowgraph flow visualization of isolated tiltrotor and rotor/wing wakes (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 2 (A93-35901 14-01); p. 1323-1344.
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  • 21
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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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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 697-719.
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  • 22
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    Numerical simulation of a hovering rotor using embedded grids (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 429-445.
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  • 23
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    A finite-volume Euler solver for computing rotary-wing aerodynamics on unstructured meshes (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: In: AHS, Annual Forum, 48th, Washington, June 3-5, 1992, Proceedings. Vol. 1 (A93-35901 14-01); p. 419-428.
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  • 24
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    Development of the wake of an airfoil with riblets (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 12; p. 2817, 2818. Abrid
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  • 25
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    Unsteady simulation of viscous flowfield around F-18 aircraft at large incidence (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 6; p. 986-992.
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  • 26
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    Study on vortex flow control of inlet distortion (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 6; p. 1266-1272.
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  • 27
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    Navier-Stokes simulation of a close-coupled canard-wing-body configuration (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 830-838
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  • 28
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    Aeroelastic effects of spoiler surfaces on a low-aspect-ratio rectangular wing (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 768-773
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  • 29
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    Assessment of compressibility corrections to the k-epsilon model in high-speed shear layers (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 10, O; 2369
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  • 30
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    Plasmadynamic effects in thermochemical nonequilibrium aerobrake flows (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 3, Ma; 319-326
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  • 31
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    Computation of saddle point of attachment (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1561-156
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  • 32
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    Transonic Navier-Stokes computations for an oscillating wing using zonal grids (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 3, Ma; 326-335
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    Tangential, semisubmerged, and internal store carriage and separation (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
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    Bodies with noncircular cross sections and bank-to-turn missiles (1992)
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    Publication Date: 2011-08-24
    Description: 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.
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    Low aspect ratio wings at high angles of attack (1992)
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    Publication Date: 2011-08-24
    Description: 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.
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    Computational methods for shock waves in three-dimensional supersonic flow (1991)
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    Publication Date: 2011-08-24
    Description: A central artificial-viscosity and an upwind-biased difference method are contrived to solve the Euler equations for flowfields over typical spacecrafts. The spatial discretization is based on either nodal or cell-vertex formulation in the domain extending from free stream to the end of the vehicle. The outer boundary is treated as a bow shock in the first method but is placed in the free stream in the second, which captures both bow and internal shocks using an approximate Riemann solver based on high-order extrapolation to the cell face. These methods were tested for the Shuttle and Hermes orbiters at wind-tunnel conditions and angles of attack ranging from 0 to 60 deg. The artificial-viscosity method incorporated with a shock-fitting procedure shows smeared crossflow and wing-shock positions and required 15 percent more CPU per node than the upwind method. Greater flexibility and robustness is demonstrated by the latter on a fixed grid for all cases considered.
    Keywords: AERODYNAMICS
    Type: Computer Methods in Applied Mechanics and Engineering (ISSN 0045-7825); 87; 2-3,
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    Numerical study of the effects of reverse sweep on scramjet inlet performance (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 3, Ma; 714-719
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    Evaluation of a finite volume method for compressible shear layers (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 5, Ma; 1214-121
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  • 39
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    Application of the LAURA code for slender-vehicle aerothermodynamics (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 16-23
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  • 40
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    Implicit Navier-Stokes solver for three-dimensional compressible flows (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 11; p. 2653-2659.
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  • 41
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    Comparison of algebraic turbulence models for afterbody flows with jet exhaust (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 11; p. 2716-2722.
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  • 42
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    Application of an unsteady Navier-Stokes solver to transonic turbine design (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 5, Se; 1079-108
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  • 43
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    Gortler instability and supersonic quiet nozzle design (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 8, Au; 2093
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  • 44
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    Predicted pressure distribution on a prop-fan blade through Euler analysis (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 627-631
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  • 45
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    Navier-Stokes computations on swept-tapered wings, including flexibility (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 588-597
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  • 46
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    Navier-Stokes predictions for the F-18 wing and fuselage at large incidence (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 4, Ju; 565-574
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  • 47
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    Aerothermodynamics of a 1.6-meter-diameter sphere in hypersonic rarefied flow (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 7, Ju; 1789-179
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  • 48
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    Domain-decomposition algorithm applied to multielement airfoil grids (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1457-146
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  • 49
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    Effect of acoustic excitation on stalled flows over an airfoil (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1492-149
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  • 50
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    Two- and three-dimensional grid generation by an algebraic homotopy procedure (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 5, Ma; 1433
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    Navier-Stokes solution of transonic cascade flows using nonperiodic C-type grids (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 34; 473-483
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    Enthalpy damping for high Mach number Euler solutions (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 300
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  • 54
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    Flow over an all-body hypersonic aircraft - Experiment and computation (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 920-926
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    Two-fence concept for efficient trapping of vortices on airfoils (1992)
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    Publication Date: 2011-08-24
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se
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    Euler/experiment correlation of a generic fighter (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 839-846
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    Unsteady shock-vortex interaction on a flexible delta wing (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 5, Se; 790-798
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    Application of a parallel direct simulation Monte Carlo method to hypersonic rarefied flows (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 9, Se; 2212-221
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    Modern developments in shear flow control with swirl (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 973-981
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    Computational study of incipient leading-edge separation on a supersonic delta wing (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 288
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    Correction of sideslip-induced static pressure errors in flight-test measurements (1992)
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: 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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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 101-107
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    Numerical simulation of entry flow over blunt swept-wing planes (1992)
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    Publication Date: 2011-08-24
    Description: Viscous, heat-conducting flow with chemical and vibrational relaxation processes of the constituent gases surrounding winged spacecraft is considered in the continuum regime. The Navier-Stokes equations are appended by additional vibrational energy and species rate equations and supplemented by the equations of state and the phenomenological laws based on mixture rules or collisional cross sections. Numerical convective flux can be obtained from several forms of one-dimensional Riemann solver, with or without entropy correction. High-order accuracy is obtained from two types of reconstructive interpolation. A number of explicit and implicit numerical schemes have been implemented as a means to yield converged solutions. Both shock-fitting, finite-difference and shock-capturing, finite-volume techniques have been tested for configurations such as a sphere, double ellipsoid, blunt-edge delta wing, a European Hermes vehicle, and the U.S. Shuttle Orbiter. The shock-fitting code provides excellent results only for simple configurations, whereas the shock-capturing code leads to overall satisfying solutions for complex geometries.
    Keywords: AERODYNAMICS
    Type: In: Advances in hypersonics. Vol. 3 - Computing hypersonic flows (A94-10767 01-02); p. 220-298.
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    Modeling of hypersonic reacting flows (1992)
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    Publication Date: 2011-08-24
    Description: The effect of nonequilibrium thermochemical processes on the aerodynamic and heat transfer characteristics of a hypersonic vehicle is illustrated with examples. It is shown that the conventional method of predicting chemical reactions always predict that the flow is closer to equilibrium than it actually is, leading to incorrect predictions of aerodynamic characteristics of a vehicle. A method is presented for predicting chemical processes using a two-temperature kinetic model, which is developed on the basis of combining conservation equations for vibrational energy and for electron electronic energy, which are also derived. The validity of the two-temperature model is proven using two types of experimental data: radiation and shock shapes.
    Keywords: AERODYNAMICS
    Type: In: Advances in hypersonics. Vol. 2 - Modeling hypersonic flows (A94-10759 01-02); p. 104-127.
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    Wall catalytic recombination and boundary conditions in nonequilibrium hypersonic flows - With applications (1992)
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    Publication Date: 2011-08-24
    Description: The meaning of catalysis and its relation to aerodynamic heating in nonequilibrium hypersonic flows are discussed. The species equations are described and boundary conditions for them are derived for a multicomponent gas and for a binary gas. Slip effects are included for application of continuum methods to low-density flows. Measurement techniques for determining catalytic wall recombination rates are discussed. Among them are experiments carried out in arc jets as well as flow reactors. Diagnostic methods for determining the atom or molecule concentrations in the flow are included. Results are given for a number of materials of interest to the aerospace community, including glassy coatings such as the RCG coating of the Space Shuttle and for high temperature refractory metals such as coated niobium. Methods of calculating the heat flux to space vehicles in nonequilibrium flows are described. These methods are applied to the Space Shuttle, the planned Aeroassist Flight Experiment, and a hypersonic slender vehicle such as a transatmospheric vehicle.
    Keywords: AERODYNAMICS
    Type: In: Advances in hypersonics. Vol. 2 - Modeling hypersonic flows (A94-10759 01-02); p. 176-250.
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    Turbulence modeling for hypersonic flows (1992)
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    Publication Date: 2011-08-24
    Description: Turbulence modeling for high-speed compressible flows is described and discussed. Starting with the compressible Navier-Stokes equations, methods of statistical averaging are described by means of which the Reynolds-averaged Navier-Stokes equations are developed. Unknown averages in these equations are approximated using various closure concepts. Zero-, one-, and two-equation eddy viscosity models, algebraic stress models, and Reynolds stress transport models are discussed. Computations of supersonic and hypersonic flows obtained using several of the models are discussed and compared with experimental results. Specific examples include attached boundary-layer flows, shock-wave boundary-layer interactions, and compressible shear layers. From these examples, conclusions regarding the status of modeling and recommendations for future studies are discussed.
    Keywords: AERODYNAMICS
    Type: In: Advances in hypersonics. Vol. 2 - Modeling hypersonic flows (A94-10759 01-02); p. 1-43.
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    Fluid/chemistry modeling for hypersonic flight analysis (1992)
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    Publication Date: 2011-08-24
    Description: Design studies are underway for a variety of hypersonic flight vehicles. The National Aero-Space Plane will provide a reusable, single-stage-to-orbit capability for routine access to low earth orbit. Flight-capable satellites will dip into the atmosphere to maneuver to new orbits, while planetary probes will decelerate at their destination by atmospheric aerobraking. To supplement limited experimental capabilities in the hypersonic regime, computational fluid dynamics is being used to analyze the flow about these configurations. The governing equations include fluid dynamic as well as chemical species equations, which are being solved with new, robust numerical algorithms. Examples of CFD applications to hypersonic vehicles suggest an important role this technology will play in the development of future aerospace systems. The computational resources needed to obtain solutions are large, but solution-adaptive grids, convergence acceleration, and parallel processing may make run times manageable.
    Keywords: AERODYNAMICS
    Type: Computers and Mathematics with Applications (ISSN 0097-4943); 24; 5-6; p. 25-36.
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  • 77
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    Vortical flow computations on a flexible blended wing-body configuration (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 10, O; 2497-250
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  • 78
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    Mixing studies of helium in air at high supersonic speeds (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 9, Se; 2234-224
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  • 79
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    Multiple shock-shock interference on a cylindrical leading edge (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 8, Au; 2073-207
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  • 80
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    Hypersonic rarefied flow about a delta wing - direct simulation and comparison with experiment (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 8, Au; 2017-202
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  • 81
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    High-Reynolds-number test requirements in low-speed aerodynamics (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Research requirements to an ultra-high-Reynolds-number liquid helium facility are reviewed. Aerodynamic research areas under consideration include wave vortex hazard reduction, vortex control and diagnostics for maneuvering fighter aircraft, and performance of high-lift devices.
    Keywords: AERODYNAMICS
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  • 82
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    Numerical analysis of flow through oscillating cascade sections (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 4, Ju; 815-822
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  • 83
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    Bleed-boundary conditions for numerically simulated mixed-compression supersonic inlet flow (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: A numerical study was performed to investigate boundary conditions for bleed openings that are needed in the numerical simulation of critical flow through turbojet inlets with bleed. Nine different boundary conditions (BCs) were devised and examined. Of the BCs examined, three were able to stabilize the terminal shock near the inlet's throat. This numerical study was based on the ensemble-averaged, unsteady, three-dimensional, compressible Navier-Stokes equations closed by the Baldwin-Lomax algebraic turbulence model. Solutions to the Navier-Stokes equations were obtained by using a hybrid implicit-explicit method (Beam and Warming/MacCormack). The multiblock grid system used in the solution procedure was generated by solving a set of elliptic partial differential equations. Solutions obtained were compared with available experimental data.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 4, Ju
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  • 84
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    Thermochemical nonequilibrium flow computations of flow around the aeroassist flight experiment (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 6; 3, Ju; 405-411
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  • 85
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    Subsonic and transonic low-Reynolds-number airfoils with reduced pitching moments (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 3, Ma; 297
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  • 86
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    Supersonic full-potential methods for missile body analysis (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Accounts are presented of representative applications to missile bodies of arbitrary shape of methods based on the steady form of the full potential equation. The NCOREL and SIMP full-potential codes are compared, and their results are evaluated for the cases of an arrow wing and a wing-body configuration. Attention is given to the effect of cross-sectional and longitudinal geometries. Comparisons of surface pressure and longitudinal force and moment data for circular and elliptic bodies have shown that the full-potential methods yielded excellent results in attached-flow conditions. Results are presented for a conical star body, waveriders, the Shuttle Orbiter, and a highly swept wing-body cruising at Mach 4.
    Keywords: AERODYNAMICS
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  • 87
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    Paneling methods with vorticity effects and corrections for nonlinear compressibility (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Supersonic panel methods and axisymmetric body-modeling singularity methods are presently combined with corrections for nonlinear flow phenomena to a complete missile, its airbreathing inlets, and wing-body combinations. The computer code LRCDM2 is used as an illustrative example of the methods in question. Attention is given to a preliminary method which employs panels to estimate additive drag and lift acting on supersonic rectangular inlets, as well as to the method used to correct off-body flowfields for the presence of a shock. Examples of missile applications of these methods with the appropriate nonlinear corrections are presented.
    Keywords: AERODYNAMICS
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  • 88
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    Vortex cloud model for body vortex shedding and tracking (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: The present engineering prediction method addresses the aerodynamic characteristics and associated flowfields of circular and noncircular bodies at large incidence angles and arbitrary roll angles. 3D attached-flow models are used to represent the body, and 2D, incompressible, separated flow models are used to represent the separated vortex wake. The predicted pressure distribution of the body, under the influence of both the freestream and the separation vortex wake, is used to calculate aerodynamic loads. The separation vortex wake is represented by clouds of discrete vortices in crossflow planes normal to the body axis.
    Keywords: AERODYNAMICS
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  • 89
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    Numerical studies of transverse curvature effects on transonic flow stability (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: A numerical study of transverse curvature effects on compressible flow temporal stability for transonic to low supersonic Mach numbers is presented for axisymmetric modes. The mean flows studied include a similar boundary-layer profile and a nonsimilar axisymmetric boundary-layer solution. The effect of neglecting curvature in the mean flow produces only small quantitative changes in the disturbance growth rate. For transonic Mach numbers (1-1.4) and aerodynamically relevant Reynolds numbers (5000-10,000 based on displacement thickness), the maximum growth rate is found to increase with curvature - the maximum occurring at a nondimensional radius (based on displacement thickness) between 30 and 100.
    Keywords: AERODYNAMICS
    Type: Physics of Fluids A (ISSN 0899-8213); 4; 5, Ma
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  • 90
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    Earth atmospheric entry studies for manned Mars missions (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 6; 193-199
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  • 91
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    Comparison of heating calculations with experimental data on a modified Shuttle Orbiter (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 208-215
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  • 92
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    Computation of near-wake, aerobrake flowfields (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 182-189
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  • 93
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    Numerical simulation of vortex unsteadiness on a slender body at high incidence (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Numerical results obtained with the present3D thin-layer Navier-Stokes solver are shown to qualitatively follow experimental results. They also indicate the existence of at least two main frequencies on an ogive cylinder at 40 and 60 deg angles-of-attack: (1) a low frequency associated with fluctuations of the primary vortices, and leads to vortex shedding, and (2) a high frequency associated with shear-layer fluctuations that are concentrated in several small areas above the leeward side of the body's cylindrical portion.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 841-843
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  • 94
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    Unsteady Euler analysis of the flowfield of a propfan at an angle of attack (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 136-143
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  • 95
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    Surface flow patterns on an ogive-cylinder at incidence (1992)
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    Publication Date: 2011-08-24
    Description: A set of photographs has been obtained which documents the oil-imaged surface flow patterns of an ogive-cylinder at angles-of-attack between 30 and 85 deg, and Reynolds number of 26,000. Attention is given to the possibility that the bistable nature of the flow within the 50-65 deg angle-of-attack range is linked to the coincident appearance of foci in the surface flow patterns, in view of the suggestion that these foci act as the anchor points allowing the forebody vortical structures to roll up and form the forebody's trailing vortex system.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 272-274
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  • 96
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    Measurements of the flow around a lifting-wing/body junction (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Detailed measurements of all three mean velocity components and five of the six Reynolds stresses have been made around a model of a lifting-wing/body junction. The body was the flat working section floor of a small blower wind tunnel. Measurements of the surface pressure distribution on the NACA 0012 wing showed that the lift coefficient at the body surface was reduced by only 16 percent from the freestream value. It is shown that the near constancy of the bound vorticity requires the formation of aixal vorticity within the body boundary layer. This vorticity was concentrated in the two legs of the necklace vortex formed near the leading edge of the wing. The magnitude of the vorticity was always greater in the leg that developed on the suction surface. By four chord lengths downstream of the trailing edge, the turbulence structure of the suction leg was qualitatively similar to that of a single vortex imbedded in a turbulent boundary layer.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6-12
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  • 97
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    Engineering calculations of three-dimensional inviscid hypersonic flowfields (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 628-635
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  • 98
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    Static aeroelastic analysis for generic configuration wing (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: A static aeroelastic analysis capability that calculates flexible air loads for generic configuration wings was developed. It was made possible by integrating a finite element structural analysis code (MSC/NASTRAN) and a panel code of aerodynamic analysis based on linear potential flow theory. The framework already built in MSC/NASTRAN was used, and the aerodynamic influence coefficient matrix was computed externally and inserted in the NASTRAN by means of a DMAP program. It was shown that deformation and flexible air loads of an oblique wing configuration including asymmetric wings can be calculated reliably by this code both in subsonic and supersonic speeds.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 801
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  • 99
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    Numerical prediction of subsonic turbulent flows over slender bodies at high incidence (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 2054-206
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  • 100
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    Three-dimensional boundary-layer transition on a cone at Mach 3.5 (1992)
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    Publication Date: 2011-08-24
    Description: A boundary-layer transition study on a sharp, 5 deg half-angle cone at various angles of attack was conducted at Mach 3.5. Transition data were obtained with and without significantly reduced freestream acoustic disturbance levels. A progressive downstream and upstream motion of the transition front on the windward and leeward rays, respectively, of the cone with angle of attack was observed for the high noise level data in agreement with data trends obtained in conventional ('noisy') wind tunnels. However, the downstream movement was not observed to the same degree for the low noise level data in the present study. Transition believed to be crossflow dominated was found to be less receptive to freestream acoustic disturbances than first-mode (Tollmien-Schlichting) dominated transition. The previously-developed crossflow transition Reynolds number criterion was found to be inadequate for the current case. An improved criterion is offered, which includes compressibility and flow-geometry effects.
    Keywords: AERODYNAMICS
    Type: Experiments in Fluids (ISSN 0723-4864); 13; 5; p. 305-314.
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