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  • FLUID MECHANICS AND HEAT TRANSFER  (67)
  • 1980-1984  (67)
  • 1960-1964
  • 1983  (67)
  • 1
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    Mean flowfields in axisymmetric combustor geometries with swirl (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: (Previously cited in issue 06, p. 860, Accession no. A82-17824)
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 2
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    Spectral methods for the Euler equations (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Spectral methods for compressible flows are introduced in relation to finite difference and finite element techniques within the framework of the method of weighted residuals. Current spectral collocation methods are put in historical context. The basic concepts of both Fourier and Chebyshev spectral collocation methods are provided. Filtering strategies for both shock-fitting and shock-capturing approaches are also presented. Fourier shock capturing techniques are evaluated using a one-dimensional, periodic astrophysical 'nozzle' problem. Examples of shock-fitting approaches include a shock/acoustic wave interaction, shock/vortex interaction, and the classical blunt body problem. While the shock capturing spectral method does not yet show a clear advantage over second-order finite differences, equivalent accuracy can be obtained using shock fitting with far fewer grid points.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 83-1942
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  • 3
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    Analytical and Experimental Evaluation of the Heat Transfer Distribution over the Surfaces of Turbine Vanes (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three airfoil data sets were selected for use in evaluating currently available analytical models for predicting airfoil surface heat transfer distributions in a 2-D flow field. Two additional airfoils, representative of highly loaded, low solidity airfoils currently being designed, were selected for cascade testing at simulated engine conditions. Some 2-D analytical methods were examined and a version of the STAN5 boundary layer code was chosen for modification. The final form of the method utilized a time dependent, transonic inviscid cascade code coupled to a modified version of the STAN5 boundary layer code featuring zero order turbulence modeling. The boundary layer code is structured to accommodate a full spectrum of empirical correlations addressing the coupled influences of pressure gradient, airfoil curvature, and free-stream turbulence on airfoil surface heat transfer distribution and boundary layer transitional behavior. Comparison of pedictions made with the model to the data base indicates a significant improvement in predictive capability.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-168015 , NAS 1.26:168015 , EDR-11209
    Format: application/pdf
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  • 4
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    Preliminary rotor wake measurements with a laser velocimeter (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A laser velocimeter (LV) was used to determine rotor wake characteristics. The effect of various fuselage widths and rotor-fuselage spacings on time averaged and detailed time dependent rotor wake velocity characteristics was defined. Definition of time dependent velocity characteristics was attempted with the LV by associating a rotor azimuth position with each velocity measurement. Results were discouraging in that no apparent time dependent velocity characteristics could be discerned from the LV measurements. Since the LV is a relatively new instrument in the rotor wake measurement field, the cause of this lack of periodicity is as important as the basic research objectives. An attempt was made to identify the problem by simulated acquisition of LV-type data for a predicted rotor wake velocity time history. Power spectral density and autocorrelation function estimation techniques were used to substantiate the conclusion that the primary cause of the lack of time dependent velocity characteristics was the nonstationary flow condition generated by the periodic turbulence level that currently exists in the open throat configuration of the wind tunnel.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-83246 , L-15080 , NAS 1.15:83246 , AVRADCOM-TR-82-B-7
    Format: application/pdf
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  • 5
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    Use of CYBER 203 and CYBER 205 computers for three-dimensional transonic flow calculations (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiences are discussed for modifying two three-dimensional transonic flow computer programs (FLO 22 and FLO 27) for use on the CDC CYBER 203 computer system. Both programs were originally written for use on serial machines. Several methods were attempted to optimize the execution of the two programs on the vector machine: leaving the program in a scalar form (i.e., serial computation) with compiler software used to optimize and vectorize the program, vectorizing parts of the existing algorithm in the program, and incorporating a vectorizable algorithm (ZEBRA I or ZEBRA II) in the program. Comparison runs of the programs were made on CDC CYBER 175. CYBER 203, and two pipe CDC CYBER 205 computer systems.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84604 , L-15553 , NAS 1.15:84604
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  • 6
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    Turbulence measurements in confined jets using a rotating single-wire probe technique (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 18, p. 2885, Accession no. A82-37710
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 21; 1609
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  • 7
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    Aerodynamically-driven condensate layer thickness distributions on isothermal cylindrical surfaces (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A simple yet rather general mathematical model is presented for predicting the distribution of condensate layer thickness when aerodynamic shear is the dominant mechanism of liquid flow along the surface. The Newtonian condensate film is treated using well-known thin-layer (lubrication theory) approximations, and condensate supply is taken to be the result of either convective diffusion or inertial impaction. Illustrative calculations for a circular cylinder in a crossflow at Re = 100,000 reveal the consequences of alternate condensate arrival mechanisms and the existence of thicker reverse-flow films behind the position of gas boundary-layer separation. The present formulation is readily generalized to include transient liquid layer flows on noncircular objects of variable surface temperature, as encountered in turbine-blade materials testing or operation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Chemical Engineering Communications (ISSN 0098-6445); 24; 275-287
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  • 8
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    Modeling of transient two-component flow using a four-point implicit method (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The four-point, centered implicit scheme that is extensively used in open channel flow simulation is shown to be applicable to rapid and slow pressure transient problems in conduits with nearly single phase and two-phase flows. It is only necessary to choose the proper weighting factor value, theta, of the Courant number. For rapid pressure transients such as waterhammer, the implicit method can yield reasonable results with limited numerical dispersion and attenuation if theta is only slightly greater than the critical value of 0.5. For slower pressure gradients in single and two-phase flows, reasonable numerical solutions may be achieved for Courant number values as high as 20.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 9
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    A modified Dodge algorithm for the parabolized Navier-Stokes equations and compressible duct flows (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A revised version of Dodge's split-velocity method for numerical calculation of compressible duct flow was developed. The revision incorporates balancing of mass flow rates on each marching step in order to maintain front-to-back continuity during the calculation. The (checkerboard) zebra algorithm is applied to solution of the three dimensional continuity equation in conservative form. A second-order A-stable linear multistep method is employed in effecting a marching solution of the parabolized momentum equations. A checkerboard iteration is used to solve the resulting implicit nonlinear systems of finite-difference equations which govern stepwise transition. Qualitative agreement with analytical predictions and experimental results was obtained for some flows with well-known solutions. Previously announced in STAR as N82-16363
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal for Numerical Methods in Fluids (ISSN 0271-2091); 3; 493-506
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  • 10
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    Accuracy of approximations to the Navier-Stokes equations (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The systems of truncated differential equations that have been proposed to reduce the complexity and large computational costs of solutions to the full Navier-Stokes equations are considered. These systems are computationally efficient and capture all the physically relevant behavior. The systems follow a certain hierarchy: (1) the classical boundary-layer equations with specified edge properties (usually the streamwise pressure distribution); (2) the coupled boundary-layer/inviscid equations; (3) the so-called thin-layer equations that discard streamwise diffusion; and (4) the Navier-Stokes equations. Consideration is given to each of these approximations applied to an incompressible, laminar-separating flow at low and moderate Reynolds numbers. It is pointed out that for any flow or region of flow for which viscous-inviscid interaction effects are small, classical boundary-layer equations will provide a satisfactory description of the viscous flow at a fraction of the computational cost of any higher approximations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 21; 1759
    Format: text
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