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  • 1
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    Measurements of Unsteady Vortex Flowfields (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A combined surface hot film and laser velocimeter measurement technique has been developed for the study of time-dependent turbulent flows. Data obtained in a compressible cylinder wake (M(sub infinity) = 0.6) are presented, and its structure in both the Eulerian and Lagrangian frames is discussed. Turbulence data obtained by conventional and phase averaging of the velocity fluctuations provide details of the small- and large-scale contributions to the total turbulent field.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: AIAA Paper 78-18R , Aerospace Sciences; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL; United States|AIAA Journal; 18; 10; 1173-1179
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of Turbulent Boundary-Layer Separation Using Laser Velocimetry (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Boundary-layer measurements realized by laser velocimetry are presented for a Much 2.9, two-dimensional, shock-wave/turbulent boundary-layer interaction containing an extensive region of separated flow. Mean velocity and turbulent intensity profiles were obtained from upstream of the interaction zone to downstream of the mean reattachment point. The superiority of the laser velocimeter technique over pressure sensors in turbulent separated flows is demonstrated by a comparison of the laser velocimeter data with results obtained from local pilot and static pressure measurements for the same flow conditions. The locations of the mean separation and reattachment points as deduced from the mean velocity measurements are compared to oil-now visualization results. Representative velocity probability density functions obtained in the separated now region are also presented. Critical to the success of this investigation were: the use of Bragg cell frequency shifting and artificial seeding of the now with submicron light-scattering particles.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA/TM-1976-208061 , NAS 1.15:208061 , AIAA Paper 76-374 , Fluid and Plasma Dynamics; Jul 14, 1976 - Jul 16, 1976; San Diego, CA; United States|AIAA Journal; 17; 7; 747-752
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  • 3
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    Transonic Flow Past a Symmetrical Airfoil-- Inviscid and Turbulent Flow Properties (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flowfield measurements are presented for a symmetrical NACA 64A010 airfoil section at transonic conditions. Measurements were obtained for three angles of attack with the freestream Mach number fixed at O.S. The cases studied included a weak shock-wave/boundary-layer interaction, an interaction of medium strength with mild separation, and an interaction of sufficient strength to produce a shock-induced stall situation. Two nonintrusive optical techniques, lower velocimetry and holographic interferometry, were used to characterize the flows. The results include Mach number contours and flow angle distributions in the inviscid flow regions, and turbulent flow properties, including the turbulent Reynolds stresses, of the upper surface viscous layers, and of the near-wake. The turbulent flow measurements reveal that the turbulence fluctuations attain equilibrium with the local mean flow much faster than previously expected.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA/TM-79-208092 , NAS 1.15:208092 , AIAA Paper 78-1117 , AIAA Journal; 18; 1; 16-24|Fluid and Plasma Dynamics Conference; Jul 10, 1978 - Jul 12, 1978; Seattle, WA; United States
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  • 4
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    Comparison Between Experiment and Prediction for a Transonic Turbulent Separated Flow (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Solutions of the time-dependent, mass-averaged Navier-Stokes equations are compared In detail with experimental results obtained on an axisymmetric "bump" model at a transonic Mach number that produced an extensive separated now region. In addition, an inverse boundary method is evaluated for this type of flow. The Cebeci-Smith algebraic and the Wilcox-Rubesin two-equation turbulence models used in the Navier-Stokes calculations both predict the maximum boundary-layer displacement thickness generated by the interaction reasonably well, with the details of the now best described with the two-equation formulation. However, both models predict a shock location substantially farther aft on the bump than observed experimentally. This error in shock location was slightly less with the two-equation model (0.12 chord compared with 0.16 chord). In the vicinity of the shock, the calculations predict a more rapid increase in turbulent shear stress than observed in the experimental results; this more rapid increase is believed to be the cause or the poor predictions in shock position.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA/TM-1982-207873 , NAS 1.15:207873 , AIAA Paper 80-1407 , AIAA Journal; 20; 6; 737-744|Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO; United States
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