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  • 1
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    Two-component LDV investigation of three-dimensional shock/turbulent boundary-layer interactions (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 26; 52-56
    Format: text
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  • 2
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    Geometric bias and time coincidence in 3-dimensional laser Doppler velocimeter systems (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The measurement by a three-dimensional laser Doppler velocimeter of a turbulent flow has been numerically simulated. Errors associated with the probe volume geometry and the coincidence time window concept are revealed. One type of error occurs for high system data rates when multiple particles lead to system realizations. Another error occurs associated with a geometric bias discovered in the present study. This three-dimensional ldv geometric bias exists even for single-particle realizations and regardless of the system data rate. A technique for the elimination of the geometric bias is presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Experiments in Fluids (ISSN 0723-4864); 7; 1, 19
    Format: text
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  • 3
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    Turbulent properties of axisymmetric shock-wave/boundary-layer interaction flows (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A combined experimental and computational investigation of an axisymmetric turbulent shock-wave boundary-layer interaction flow is presented. Experimental measurements include both mean and fluctuating data obtained by LDV techniques and identify large scale unsteady motions associated with shock induced separation. Computations using the compressible Navier-Stokes equations, and a two-equation turbulence model are in relatively good agreement with experimental measurements. It is found that the large scale unsteady motions do not appear to have a critical impact on the ability to compute the mean properties of the flows investigated in this paper.
    Keywords: AERODYNAMICS
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  • 4
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    Separated trailing-edge flow at a transonic Mach number (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 800, Accession no. A82-17899
    Keywords: AERODYNAMICS
    Type: (ISSN 0001-1452)
    Format: text
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  • 5
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    Holographic interferometry study of an axisymmetric shock-wave/boundary-layer strong interaction flow (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 294-299
    Format: text
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  • 6
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    Visual and motion simulation techniques (1965)
    In:  CASI
    Details
    Publication Date: 2017-06-27
    Description: Visual and motion simulation techniques for manned space flight models
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: VA. POLYTECH. INST. PROC. OF THE CONF. ON THE ROLE OF SIMULATION IN SPACE TECHNOL., PT. C 〈1965〈 (SEE N69-18979 08-11)
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  • 7
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    A documentation of two- and three-dimensional shock-separated turbulent boundary layers (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A shock-related separation of a turbulent boundary layer has been studied and documented. The flow was that of an axisymmetric turbulent boundary layer over a 5.02-cm-diam cylinder that was aligned with the wind tunnel axis. The boundary layer was compressed by a 30 deg half-angle conical flare, with the cone axis inclined at an angle alpha to the cylinder axis. Nominal test conditions were P sub tau equals 1.7 atm and M sub infinity equals 2.85. Measurements were confined to the upper-symmetry, phi equals 0 deg, plane. Data are presented for the cases of alpha equal to 0. 5. and 10 deg and include mean surface pressures, streamwise and normal mean velocities, kinematic turbulent stresses and kinetic energies, as well as reverse-flow intermittencies. All data are given in tabular form; pressures, streamwise velocities, turbulent shear stresses, and kinetic energies are also presented graphically.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-101008 , A-88211 , NAS 1.15:101008
    Format: application/pdf
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  • 8
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    Two-component LDV investigation of 3-dimensional shock/turbulent boundary layer interactions (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Mean-velocity and turbulence measurements obtained by two-component laser Doppler velocimetry are presented, together with numerical predictions, for the shock-related separation of a turbulent boundary layer at Mach 2.85. The basic geometry, a 30 deg half-angle flare mounted on a long cylinder, is made three-dimensional by tipping the flare at an angle of attack, alpha. The separation length and general upstream influence increase with alpha. A recirculating vortex in the separated zone becomes stronger as three-dimensionality increases. A large-scale unsteadiness of the separation shock wave and surrounding flowfields grows in amplitude with alpha, and appears to strongly influence the amplification of turbulence correlations ahead of detachment. Scaling of the streamwise coordinate by separation length causes two-dimensional and three-dimensional data profiles on the cylinder to collapse for most measured quantities.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0553
    Format: text
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  • 9
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    An experimental documentation of a separated trailing-edge flow at a transonic Mach number (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A detailed experiment on the separated flow field at a sharp trailing edge is described and documented. The separated flow is a result of sustained adverse pressure gradients. The experiment was conducted using an elongated airfoil-like model at a transonic Mach number and at a high Reynolds number of practical interest. Measurements made include surface pressures and detailed mean and turbulence flow quantities in the region just upstream of separation to downstream into the near-wake, following wake closure. The data obtained are presented mostly in tabular form. These data are of sufficient quality and detail to be useful as a test case for evaluating turbulence models and calculation methods.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84290 , A-9074 , NAS 1.15:84290
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  • 10
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    Parabolized Navier-Stokes solutions of separation and trailing-edge flows (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A robust, iterative solution procedure is presented for the parabolized Navier-Stokes or higher order boundary layer equations as applied to subsonic viscous-inviscid interaction flows. The robustness of the present procedure is due, in part, to an improved algorithmic formulation. The present formulation is based on a reinterpretation of stability requirements for this class of algorithms and requires only second order accurate backward or central differences for all streamwise derivatives. Upstream influence is provided for through the algorithmic formulation and iterative sweeps in x. The primary contribution to robustness, however, is the boundary condition treatment, which imposes global constraints to control the convergence path. Discussed are successful calculations of subsonic, strong viscous-inviscid interactions, including separation. These results are consistent with Navier-Stokes solutions and triple deck theory.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84378 , A-9394 , NAS 1.15:84378
    Format: application/pdf
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