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  • 1
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    A summary of Reynolds number effects on some recent tests in the Langley 0.3-meter transonic cryogenic tunnel (1986)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Reynolds number effects noted from selected test programs conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT) are discussed. The tests, which cover a unit Reynolds number range from about 2.0 to 80.0 million per foot, summarize effects of Reynolds number on: (1) aerodynamic data from a supercritical airfoil, (2) results from several wall interference correction techniques, and (3) results obtained from advanced, cryogenic tests techniques. The test techniques include: (1) use of a cryogenic sidewall boundary layer removal system, (2) detailed pressure and hot wire measurements to determine test section flow quality, and (3) use of a new hot film system suitable for transition detection in a cryogenic wind tunnel. The results indicate that Reynolds number effects appear most significant when boundary layer transition effects are present and at high lift conditions when boundary layer separation exists on both the model and the tunnel sidewall.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 861765
    Format: text
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  • 2
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    Laser velocimetry for transonic aerodynamics (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Applications of laser velocimetry to the measurement of turbulent flow properties of strong transonic viscous-inviscid interactions are reviewed. The data resulting from these studies are then discussed in relation to their importance in the development of improved viscous-flow calculation methods. Also considered are the current limitations of laser velocimetry, the need for further improvements in the method, and potential future applications.
    Keywords: AERODYNAMICS
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  • 3
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    Transonic airfoil calculations including wind tunnel wall-interference effects (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The results of Reynolds-averaged time-dependent inviscid and turbulent compressible Navier-Stokes computations using the implicit finite-difference approach of Steger (1978), modified by incorporating a pressure boundary condition, (PBC) to account for wall interference are compared with experimental data on a NACA 64A010 airfoil (Johnson and Bachalo, 1980) in graphs and briefly characterized. The computational approach is the same as that used by King and Johnson (1980), but a 137 x 50 mesh is used instead of a 97 x 35 mesh, and special care is taken in resolving the nose, shock, and trailing-edge regions. Imposition of PBC is shown to improve significantly the accuracy of the computations for the flowfield on the upper surface of the airfoil, shifting the shock forward to its experimentally measured position in the case of turbulent flow. The failure of the method, even with PBC, to match the experimental shock location in the case of a flow with a separation bubble is attributed to inadequacies in the algebraic turbulence model employed (Baldwin and Lomax, 1978).
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1378-138
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  • 4
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    Recent developments in rotary-wing aerodynamic theory (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Current progress in the computational analysis of rotary-wing flowfields is surveyed, and some typical results are presented in graphs. Topics examined include potential theory, rotating coordinate systems, lifting-surface theory (moving singularity, fixed wing, and rotary wing), panel methods (surface singularity representations, integral equations, and compressible flows), transonic theory (the small-disturbance equation), wake analysis (hovering rotor-wake models and transonic blade-vortex interaction), limitations on computational aerodynamics, and viscous-flow methods (dynamic-stall theories and lifting-line theory). It is suggested that the present algorithms and advanced computers make it possible to begin working toward the ultimate goal of turbulent Navier-Stokes calculations for an entire rotorcraft.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1219-124
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  • 5
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    Transonic, turbulent boundary-layer separation generated on an axisymmetric flow model (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Experimental data describing the transonic, turbulent, separated flow generated by an axisymmetric flow model are presented. The model consisted of a circular-arc bump affixed to a straight, circular cylinder aligned with the flow direction. Measurements of the mean velocity, turbulence intensity, and Reynolds shear-stress profiles were made in the separated flow. These data revealed dramatic changes in the shear-stress levels as the flow passed through the interaction to reattachment. Behavior of the turbulence reaction to the imposed pressure gradients was examined in terms of the mixing length and the excursions of the turbulence from equilibrium.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 437-443
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  • 6
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    Aerodynamic effects of distributed spanwise blowing on a fighter configuration (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 673-679
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  • 7
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    An overview of some investigations of pressure and thermal distributions induced by trailing edge controls on hypersonic aircraft (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Detailed surface heat transfer and pressure distributions have been obtained in three-dimensional shock-wave boundary-layer interactions flow regions. The data described were obtained on fundamental shapes: planar wings with trailing edge flaps or spoilers and planar or cylindrical center bodies, representative of the aft portion of hypersonic aircraft. An overview of the work is presented; details of the projects are available in many reports in the open literature. Analytic, empiric methods are advanced for predicting the extent of separation and the increased heat transfer and pressure loads in three-dimensional separated flow regions.
    Keywords: AERODYNAMICS
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  • 8
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    Transonic separated flow prediction based on a mathematically simple, nonequilibrium turbulence closure model (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A mathematically simple, turbulence closure model designed to treat transonic airfoil flows even with massive separation is described. Numerical solutions of the Reynolds-averaged, Navier-Stokes equations obtained with this closure model are shown to agree well with experiments over a broad range of test conditions.
    Keywords: AERODYNAMICS
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  • 9
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    Comparison of supercritical airfoil flow calculations with wind tunnel results (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 1301-130
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  • 10
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    Efficient solution of the Euler and Navier-Stokes equations with a vectorized multiple-grid algorithm (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 23-32
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