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  • 1
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    Advanced measurement techniques, part 1 (1987)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: In modern laminar flow flight and wind tunnel research, it is important to understand the specific cause(s) of laminar to turbulent boundary layer transition. Such information is crucial to the exploration of the limits of practical application of laminar flow for drag reduction on aircraft. The process of transition involves both the possible modes of disturbance growth, and the environmental conditioning of the instabilities by freestream or surface conditions. The possible modes of disturbance growth include viscous, inviscid, and modes which may bypass these natural ones. Theory provides information on the possible modes of disturbance amplification, but experimentation must be relied upon to determine which of those modes actually dominates the transition process in a given environment. The results to date of research on advanced devices and methods used for the study of transition phenomena in the subsonic and transonic flight and wind tunnel environments are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Research in Natural Laminar Flow and Laminar-Flow Control, Part 2; p 317-340
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
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    A study of the effects of Reynolds number and Mach number on constant pressure coefficient jump for shock-induced trailing-edge separation (1987)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The influence of Mach and Reynolds numbers as well as airfoil and planform geometry on the phenomenon of constant shock jump pressure coefficient for conditions of shock induced trailing edge separation (SITES) was studied. It was demonstrated that the phenomenon does exist for a wide variety of two and three dimensional flow cases and that the influence of free stream Mach number was not significant. The influence of Reynolds number was found to be important but was not strong. Airfoil and planform geometric characteristics were found to be very important where the pressure coefficient jump was shown to vary with the sum of: (1) airfoil curvature at the upper surface crest, and (2) camber surface slope at the trailing edge. It was also determined that the onset of SITES could be defined as a function of airfoil geometric parameters and Mach number normal to the leading edge. This onset prediction was shown to predict the angle of onset to within + or - 1 deg accuracy or better for about 90% of the cases studied.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-4090 , NAS 1.26:4090
    Format: application/pdf
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  • 3
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    An investigation of the effects of seeding in laser velocimeter systems (1990)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: Errors in laser velocimeter measurements associated with the lag of seeding particles in subsonic and transonic flows were investigated experimentally and theoretically. In a low-speed flow, errors exceeding 5 percent were measured for particle diameters greater than 5 microns. In transonic flows, errors up to 60 percent were measured for particles with 2-3-micron diameters and up to 30 percent for 1-2-micron particles. A three-dimensional method was developed to determine the magnitude of errors due to the lag in seeding particle response based on a simplified particle force balance model and an empirical coefficient of drag model for spherical bodies. A one-dimensional version of this model was shown to be successful in correcting velocity measurements in both the subsonic and transonic flow regions.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 90-0502
    Format: text
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  • 4
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    Flow quality measurements for the Langley 8-foot transonic pressure tunnel LFC experiment (1989)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Laminar flow experiments were performed in an 8-foot transonic pressure tunnel which was modified in order to simulate the conditions of an infinite span yawed wing. A liner in the tunnel provided a flow field around the yawed airfoil. The results were evaluated using hot-wire and fluctuating pressure measurements. Data were obtained for root-mean-square fluctuations, their spectra, and various cross product terms.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 89-0150
    Format: text
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  • 5
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    Performance characteristics from wind-tunnel tests of a low-Reynolds-number airfoil (1988)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: Wind tunnel lift and pitching-moment data have been obtained from pressure measurements, and drag data from wake surveys, for an Eppler 387 low Reynolds number airfoil over the Re range of 60,000 to 460,000; oil flow visualizations were also used to determine laminar separation and turbulent reattachment locations. Airfoil performance is found to be dominated by laminar separation bubbles below Re 200,000, and two flow regimes, namely laminar separations with and without turbulent reattachment, were observed at the same angle-of-attack for an Re of 60,000.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 88-0607
    Format: text
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  • 6
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    Low-speed aerodynamic characteristics of a twin-engine general aviation configuration with aft-fuselage-mounted pusher propellers (1987)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was conducted to determine the aerodynamic characteristics of an advanced turboprop aircraft model with aft-pylon-mounted pusher propellers. Tests were conducted through an angle-of-attack range of -8 to 28 degrees, and an angle-of-sideslip range of -20 to 20 degrees at free-stream conditions corresponding to Reynolds numbers of 0.55 to 2.14 x 10 to the 6th power based on mean aerodynamic chord. Test results show that for the unpowered configurations the maximum lift coefficients for the cruise, takeoff, and landing configurations are 1.45, 1.90, and 2.10, respectively. Nacelle installation results in a drag coefficient increase of 0.01. Increasing propeller thrust results in a significant increase in lift for angles of attack above stall and improves the longitudinal stability. The cruise configuration remains longitudinally stable to an angle of attack 5 degrees beyond the stall angle, the takeoff configuration is stable 4 degrees beyond stall angle, and the landing configuration is stable 3 degrees beyond stall angle. The predominant effect of symmetric thrust on the lateral-directional aerodynamic characteristics is in the post-stall region, where additional rudder control is available with power on.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-2763 , L-16331 , NAS 1.60:2763
    Format: application/pdf
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  • 7
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    In-flight detection of Tollmien-Schlichting instabilities in laminar flow (1987)
    In:  Other Sources
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    Publikationsdatum: 2019-06-28
    Beschreibung: This paper presents the results of a recent flight experiment conducted to evaluate surface-mounted hot-film sensors designed to detect Tollmien-Schlichting instability in the boundary layer in flight. Flight data are presented to illustrate the design and operation of the sensors and to provide information on disturbance growth and transition mode. The results of calculations using a boundary-layer analysis code and boundary-layer linear stability analysis methods are included.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: SAE PAPER 871016
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Study of compressible mixing layers using filtered Rayleigh scattering based visualizations (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Filtered Rayleigh scattering-based flow visualizations of compressible mixing layers are reported. The lower compressibility case (Mc = 0.51) displays well-defined roller-type spanwise structures and streamwise streaks. The structures of the high compressibility case (Mc = 0.86) are more 3D and oblique.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA Journal (ISSN 0001-1452); 30; 10
    Format: text
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  • 9
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    A study of compressible mixing layers using filtered Rayleigh scattering (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: High Reynolds number compressible planar free shear layers were studied using a planar laser visualization technique. Two convective Mach numbers, M(c) = 0.51 and 0.86, were studied in the developing and fully developed regions. The structures in the M(c) = 0.51 case were characterized by 2D core and roller regions, similar to subsonic shear layers. Also for the M(c) = 0.51 case, plan views in the developing region showed the existence of streamwise streaks, possibly indicating the presence of organized streamwise vorticity. The M(c) = 0.86 flow was much less organized than the lower convective Mach number case and highly three dimensional.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 92-0175 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 06, 1992 - Jan 09, 1992; Reno, NV; United States|; 11 p.
    Format: text
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  • 10
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    Application of an unstructured grid flow solver to planes, trains and automobiles (1993)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Rampant, an unstructured flow solver developed at Fluent Inc., is used to compute three-dimensional, viscous, turbulent, compressible flow fields within complex solution domains. Rampant is an explicit, finite-volume flow solver capable of computing flow fields using either triangular (2d) or tetrahedral (3d) unstructured grids. Local time stepping, implicit residual smoothing, and multigrid techniques are used to accelerate the convergence of the explicit scheme. The paper describes the Rampant flow solver and presents flow field solutions about a plane, train, and automobile.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 93-0889 , ; 11 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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