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  • FLUID MECHANICS AND HEAT TRANSFER  (267)
  • 2015-2019
  • 1975-1979  (267)
  • 1945-1949
  • 1975  (267)
  • 1
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    Investigation B: Laminar confined coaxial entrance flow with heat generation (1975)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: The results of a parametric study on the entrance flow region in a gas core nuclear reactor are presented. The physical system is modeled as laminar confined, coaxial flow with heat generation in the inner fluid. The governing equations include the boundary layer approximations and the assumptions of only radial radiative transport of energy represented as an energy diffusion term. The Von Mises transformation and a zeta transformation are used to transform the equations into nonlinear nonhomogeneous convective-diffusion equations. A unique combination of forward and backward difference equations which yields accurate results at moderate computational times, is used in the numerical method. Results show that the rapidly accelerating, heat generating inner stream actually shrinks in radius as it expands axially.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Turbulence Coefficients and Stability Studies for the Coaxial Flow or Dissimiliar Fluids; 76 p
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  • 2
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    Empirical correlations for heat transfer and flow friction characteristics of rectangular offset-fin plate-fin heat exchangers (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 3
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    Inviscid interpenetration of two streams with unequal total pressures (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A theory is proposed for analyzing the inviscid interpretation of two streams in the case when the difference in total pressure between the streams is relatively small. A stream is considered which discharges from a nozzle or reservoir into a partially moving and partially stationary environment in such a way that the flows leave the solid boundaries in a tangential direction where the two streams first interact. The problem is solved by expanding in a small parameter related to the difference in total pressure between the streams, the zeroth-order solution is obtained by classical methods, and a technique similar to that employed in thin-airfoil theory is used to transfer the first-order boundary conditions to the zeroth-order boundary. A procedure is developed to transform the problem into one that can be solved by standard techniques of the theory of sectionally analytic functions. Solutions are obtained for flows with and without free streamlines, and the general theory is applied to several specific flow configurations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 70; Aug. 12
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  • 4
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    Radiation exchange for a system with partially transmitting wall (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An approach is presented for applying the net radiation method developed by Siegel and Howell (1972) and Sparrow and Cess (1966) to systems involving opaque and partially transmitting walls. The results obtained from the basic equations for various values of plate emissivities and temperatures are presented in graphs. Attention is given to the window temperature relative to the temperature of the hot wall and the heat transferred relative to that transferred without the window.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Letters in Heat and Mass Transfer; 2; Mar
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  • 5
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    Derivation and application of the reciprocity relations for radiative transfer with internal illumination (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A Green's function formulation is used to derive basic reciprocity relations for planar radiative transfer in a general medium with internal illumination. Reciprocity (or functional symmetry) allows an explicit and generalized development of the equivalence between source and probability functions. Assuming similar symmetry in three-dimensional space, a general relationship is derived between planar-source intensity and point-source total directional energy. These quantities are expressed in terms of standard (universal) functions associated with the planar medium, while all results are derived from the differential equation of radiative transfer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 15; Sept
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  • 6
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    Radiation from an array of longitudinal fins of triangular profile (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Radiation from an array of longitudinal fins of triangular profile is analyzed, including fin-to-fin and fin-to-base interactions. The effect of base cylinder radiation and the fin-base radiative interaction is found to be significant for fin width/tube radius ratios less than 8. Results presented may be used to optimize the design of a fin array with respect to weight.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; May 1975
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  • 7
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    Comment on 'subsonic and supersonic boundary-layer flow past a wavy wall' (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; Apr. 197
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  • 8
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    Comparison of theory and experiment for homogeneous turbulence with shear (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Solutions for uniformly-sheared turbulence, in which the interaction of the turbulence with the mean shear dominates the turbulent self-interaction, are compared with experiment. An anisotropic spectral tensor, which appears general enough to represent the initial experimental turbulence, is used for the initial condition in the calculations. The evolution of one-point turbulence components and microscales, as well as two-point velocity correlations, are considered. In most cases the agreement with experiment is good. The theory correctly predicts the presence of a negative region for two-point longitudinal-velocity correlations only for point separations in the direction normal to the flow and the mean gradient.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 18; Oct. 197
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  • 9
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    Influence of probe geometry on pitot-probe displacement in supersonic turbulent flow (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An experiment was conducted to determine the varying effects of six different probe-tip and support-shaft configurations on pitot tube displacement. The study was stimulated by discrepancies between supersonic wind-tunnel tests conducted by Wilson and Young (1949) and Allen (1972). Wilson (1973) had concluded that these discrepancies were caused by differences in probe geometry. It is shown that in fact, no major differences in profiles of streamwise velocity over streamwise velocity at boundary-layer edge vs normal coordinate over boundary-layer total thickness result from geometry. The true cause of the discrepancies, however, remains to be discovered.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; July 197
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  • 10
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    Flow rates for sharp-edged orifices (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Two charts are proposed for calculating the flow coefficient and the area correction factor used in the equation for the flow rate through a sharp-edged orifice. The proposed charts account for variations in the discharge coefficient of sharp-edged orifices and can be used with any pressure ratio for both subcritical and supercritical flow conditions. They can also be used for any gas by using the appropriate gas constant and ratio of specific heats. The application of the charts is illustrated by examples.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Machine Design; 47; June 12
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  • 11
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    Radiative equilibrium in a rectangular enclosure bounded by gray walls (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Two-dimensional temperature and heat-flux distributions are calculated for an absorbing-emitting gray medium at radiative equilibrium in a rectangular enclosure. The bounding walls are gray and diffuse with arbitrary surface-temperature distributions, and heat generation may take place inside the medium. As a first approximation, the problem is solved for optically thick systems (differential approximation). These results are subsequently improved by the introduction of a number of geometrical parameters to yield good accuracy for all optical thicknesses. As examples, two cases are discussed in detail: (1) uniform heat generation in a black enclosure, and (2) an enclosure with one gray surface at constant temperature. Comparison with some numerical solutions generated by Hottel's /Hottel and Cohen (1958) and Einstein (1963)/ zonal method shows excellent agreement.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 15; June 197
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  • 12
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    Investigation A: Numerical solutions of driven vortices of binary fluid in a cylindrical geometry (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The steady state laminar motion of a viscous, incompressible and binary fluid is studied for a rotating flow in a cylindrical geometry. The mathematical model employed is a cold flow simulation of the fluid mechanics of the light-bulb concept of the gaseous core nuclear engine. A numerical treatment is developed for the rotating flow which includes a description of the nuclear fuel addition. The problem is formulated with the complete Navier-Stokes equations in order to show the interaction between the fuel addition, the main flow, and the boundary layer flow in an accurate manner. The results presented show holdup of the nuclear fuel for the case of steady fuel addition.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Turbulence Coefficients and Stability Studies for the Coaxial flow or Dissimiliar Fluids; 146 p
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  • 13
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    Supersonic Mixing and Combustion in Parallel Injection Flow Fields (1975)
    In:  CASI
    Details
    Publication Date: 2011-01-13
    Description: Adequate prediction techniques for supersonic, mixing, reacting flows are of great importance in the design and performance analysis of supersonic combustion ramjet (scramjet) engines. Analytical programs for parallel injection flow fields with chemical reaction and turbulent mixing are now available for both single and multiple-jet flows. The application of these analyses to simple flow geometries is discussed, and comparisons also are made with data on the more complex case of multiple-jet, reacting flows. A review is given of Langley investigations of parallel injection flow fields. Among these are single-jet studies of nonreacting, turbulent mixing (H2 in air and H2 in N2), and of reacting turbulent mixing (H2 in air) with both single and multiple jets. Implications of the results of the studies for scramjet fuel injector design are discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Anal. and Numerical Methods for Invest. of Flow Fields with Chem. Reactions, Especially Related to Combust.; 8 p
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  • 14
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    Higher order accurate difference solutions of fluid mechanics problems by a compact differencing technique (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A general fourth order differencing scheme is developed and applied to three viscous test problems to verify the accuracy and applicability of the technique. The procedure is atypical since only three nodes are necessary to obtain the desired fourth order accuracy. This is accomplished by a differencing technique which considers the function and all necessary derivatives as unknowns. The relations for these derivatives yield simple tridiagonal equations which can be easily solved. Comparisons of the fourth order results with those computed using second order methods are presented for the test problems and clearly indicate that the accuracy achieved by these fourth order computations is always significantly better than current second order procedures.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics; 19; Sept
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  • 15
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    Relaxation methods in fluid mechanics (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The present work considers the iterative solution of a coupled set of difference equations and examines methods that carry successive approximates to a state that is invariant with further iteration and independent of the initial guess. Methods are studied with regard to their efficiency and economy of computer resources. The basic principles of classical relaxation are set forth, with attention confined to linear elliptic equations. This discussion involves the evaluation of the spectral radius that is the magnitude of the eigenvalue with largest modulus. The subject of relaxation is then related to the study of ordinary differential equations and hyperbolic partial differential equations. Problems that occur when linearly dependent eigenvectors appear in the relaxation matrix are discussed, leading to multiply connected eigenvalues in the Jordan canonical form. Finally, a brief survey of relaxation methods used in aerodynamics is given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 16
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    Turbulence stress measurements in a nonadiabatic hypersonic boundary layer (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Turbulent shear stress and direct turbulent total heat-flux measurements have been made across a nonadiabatic, zero pressure gradient, hypersonic boundary layer by using specially designed hot-wire probes free of strain-gauging and wire oscillation. Heat-flux measurements were in reasonably good agreement with values obtained by integrating the energy equation using measured profiles of velocity and temperature. The shear-stress values deduced from the measurements, by assuming zero correlation of velocity and pressure fluctuations, were lower than the values obtained by integrating the momentum equation. Statistical properties of the cross-correlations are similar to corresponding incompressible measurements at approximately the same momentum-thickness Reynolds number.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; Dec. 197
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  • 17
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    Experimental verification of turbulent skin friction reduction with compliant walls (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Preliminary compliant wall skin friction test results obtained in a low-turbulence pressure tunnel are reported. Compliant surface skins consisted of 0.0025 cm thick mylar, stretched under tension and area-bonded or longitudinally strip-bonded with silicone rubber adhesive to polyurethane foam. Mean velocity and fluctuating survey data were obtained with a single slanted hot wire. Mean velocity profiles for the area-bonded mylar surface skins indicated up to a 20% reduction in boundary-layer thickness (and lower momentum thickness) over rigid surfaces. This reduction in boundary-layer thickness indicates that a drag reduction occurred. In addition, a 16% reduction in wall shear was evident for the mylar/compressor foam compliant surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; July 197
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  • 18
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    Stability characteristics of a single-phase free convection loop (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experiments investigating the stability characteristics of a single-phase free convection loop are reported. Results of the study confirm the contention made by previous workers that instabilities near the thermodynamic critical point can occur for ordinary fluids as well as those with unusual behavior in the near-critical region. Such a claim runs counter to traditional beliefs, but it is supported by the observation of such instabilities for water at atmospheric pressure and moderate temperatures in the present work.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 67; Jan. 14
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  • 19
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    Drag coefficient equations for small particles in high speed flows (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper determines the effect of various available drag coefficient equations on particle velocity calculations for typical two phase flows encountered in supersonic and turbulent laser velocimeter applications. The predictions of the particle drag coefficient equations are compared with experimental sphere drag data. For the laser velocimeter applications, the relative Mach number less than 2 and the relative Reynolds number less than 200 are of particular importance.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; Nov. 197
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  • 20
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    Mixing length in low Reynolds number compressible turbulent boundary layers (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper studies the effect of low Reynolds number in high-speed turbulent boundary layers on variations of mixing length. Boundary layers downstream of natural transition on plates, cones and cylinders, and boundary layers on nozzle walls without laminarization-retransition are considered. The problem of whether low Reynolds number amplification of shear stress is a result of transitional flow structure is considered. It is concluded that a knowledge of low Reynolds number boundary layer transition may be relevant to the design of high-speed vehicles.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; Aug. 197
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  • 21
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    Contribution of the National Aeronautics and Space Administration Langley Research Center (1975)
    In:  CASI
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    Publication Date: 2012-05-19
    Description: As part of a special international effort, three nozzles were designed and tested on single nacelle models in wind tunnels of several nations belonging to the North Atlantic Treaty Organization. All three of these nozzles were investigated in the Langley 16-foot transonic wind tunnel at the National Aeronautics and Space Administration's Langley Research Center. Langley Research Center also contributed theoretical calculations of the jet plume boundary and afterbody pressures. The calculations were obtained using an iterative solution which combined the inviscid Douglas Neumann method for the external flow with the method of characteristics for the flow in the jet plume. For the investigation, the nozzles were mounted on a single nacelle model 15.24 centimeters in diameter and 162.56 centimeters long. Tests were made at free stream Mach number from 0.4 to 1.2, and at Reynolds numbers per meter from 7.38 million to 13.78 million depending on the Mach number. Four types of data were recorded: afterbody pressure data, afterbody force data, model boundary layer data, and tunnel wall pressure data. The ratio of jet total pressure to free stream static pressure ranged up to 8.5. A description of the wind tunnel, model, and test procedure is included.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Improved Nozzle Testing Tech. in Transonic Flow; 9 p
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  • 22
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    Numerical techniques for the solution of the compressible Navier-Stokes equations and implementation of turbulence models (1975)
    In:  CASI
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    Publication Date: 2012-05-19
    Description: The time-splitting explicit numerical method of MacCormack is applied to separated turbulent boundary layer flow problems. Modifications of this basic method are developed to counter difficulties associated with complicated geometry and severe numerical resolution requirements of turbulence model equations. The accuracy of solutions is investigated by comparison with exact solutions for several simple cases. Procedures are developed for modifying the basic method to improve the accuracy. Numerical solutions of high-Reynolds-number separated flows over an airfoil and shock-separated flows over a flat plate are obtained. A simple mixing length model of turbulence is used for the transonic flow past an airfoil. A nonorthogonal mesh of arbitrary configuration facilitates the description of the flow field. For the simpler geometry associated with the flat plate, a rectangular mesh is used, and solutions are obtained based on a two-equation differential model of turbulence.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Computational Methods for Inviscid and Viscous Two-and-Three-Dimensional Flow Fields; 24 p
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  • 23
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    Asymptotic analytical methods in fluid mechanics related to drag prediction (1975)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Some recent theoretical work of a purely analytical nature is described which promises to provide engineering predictions for the important drag-related phenomena of flow in the stall regime. This analytical work deals with rigorous asymptotic studies of the complete Navier-Stokes equations that govern the viscous flow around any aerodynamic body under conditions where boundary layer separation takes place from the body surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 117-124
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  • 24
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    Viscous flow solutions with a cubic spline approximation (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A cubic spline approximation is used for the solution of several problems in fluid mechanics. This procedure provides a high degree of accuracy even with a nonuniform mesh, and leads to a more accurate treatment of derivative boundary conditions. The truncation errors and stability limitations of several typical integration schemes are presented. For two-dimensional flows a spline-alternating-direction-implicit (SADI) method is evaluated. The spline procedure is assessed and results are presented for the one-dimensional nonlinear Burgers' equation, as well as the two-dimensional diffusion equation and the vorticity-stream function system describing the viscous flow in a driven cavity. Comparisons are made with analytic solutions for the first two problems and with finite-difference calculations for the cavity flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Computers and Fluids; 3; Mar. 197
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  • 25
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    Numerical calculation of finite amplitude effects in unstable laminar boundary layers (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A numerical study of one stage of the transition region from laminar to turbulent flow of the boundary layer over a flat plate is performed. Benney-Lin theory is applied to the laminar profile, which is closer to that of the experiment, i.e., the Blasius profile. Several laminar profiles are studied, all belonging to the Falkner-Skan family. The flow is found to depend principally upon the disturbance spanwise wavenumber, beta, whose variation results, in some instances, in a system of counter-rotating vortices, one on top of the other, for the mean secondary flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 18; Mar. 197
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  • 26
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    Reduction of wind tunnel wall interference by controlled wall flow (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An alternate method of testing was developed in which flow through the porous walls of the tunnel was actively controlled so as to approximate free air conditions in the neighborhood of the model during the test. The amount and distribution of the controlled flow through the walls is computed using a potential flow representation of the model based on the measured lift. Theoretical analysis is presented to prove the convergence of the method to free air conditions and to substantiate the general three-dimensional theory of operation when the normal flow distribution is continuous. A two-dimensional tunnel was constructed to evaluate the concept. Results show that substantial reduction of wall interference may be achieved with relatively low values of porosity of actively controlled walls.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-119090
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  • 27
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    Analysis of screeching in a cold flow jet experiment (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The screech phenomenon observed in a one-sixtieth scale model space shuttle test of the solid rocket booster exhaust flow noise has been investigated. A critical review is given of the cold flow test data representative of Space Shuttle launch configurations to define those parameters which contribute to screech generation. An acoustic feedback mechanism is found to be responsible for the generation of screech. A simple equation which permits prediction of screech frequency in terms of basic testing parameters such as the jet exhaust Mach number and the separating distance from nozzle exit to the surface of model launch pad is presented and is found in good agreement with the test data. Finally, techniques are recommended to eliminate or reduce the screech.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-143943 , WR-75-2
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  • 28
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    Experimental study of a free turbulent shear flow at Mach 19 with electron-beam and conventional probes (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental study of the initial development region of a hypersonic turbulent free mixing layer was made. Data were obtained at three stations downstream of a M = 19 nozzle over a Reynolds range of 1.3 million to 3.3 million per meter and at a total temperature of about 1670 K. In general, good agreement was obtained between electron-beam and conventional probe measurements of local mean flow parameters. Measurements of fluctuating density indicated that peak root-mean-square (rms) levels are higher in the turbulent free mixing layer than in boundary layers for Mach numbers less than 9. The intensity of rms density fluctuations in the free stream is similar in magnitude to pressure fluctuations in high Mach number flows. Spectrum analyses of the measured fluctuating density through the shear layer indicate significant fluctuation energy at the lower frequencies (0.2 to 5 kHZ) which correspond to large-scale disturbances in the high-velocity region of the shear layer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-7981 , L-10138
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  • 29
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    Experimental evaluation of joint designs for a space-shuttle orbiter ablative leading edge (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The thermal performance of two types of ablative leading-edge joints for a space-shuttle orbiter were tested and evaluated. Chordwise joints between ablative leading-edge segments, and spanwise joints between ablative leading-edge segments and reusable surface insulation tiles were exposed to simulated shuttle heating environments. The data show that the thermal performance of models with chordwise joints to be as good as jointless models in simulated ascent-heating and orbital cold-soak environments. The suggestion is made for additional work on the joint seals, and, in particular, on the effects of heat-induced seal-material surface irregularities on the local flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-3230 , L-10020
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  • 30
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    Flat plate electrohydrodynamic heat pipe experiments (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Performance capabilities of electrohydrodynamic (EHD) flat heat pipes were investigated using Freon 113 and Freon 11 as working fluids. All of the pipes employed straight rod electrodes to form axial liquid flow channels and tranverse grooves for capillary surface wetting. Results show: (1) the EHD pipe will prime under load, (2) voltage controlled conductance can be achieved by varying the active area of the evaporator, and (3) the average evaporator conductances measured in these experiments were consistent with those obtained in other experiments with heat pipes of similar surface geometry using the same or similar working fluids.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-137707
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  • 31
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    Experiment on turbulent boundary layers on a concave wall (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The present experiment describes the behavior of a turbulent boundary layer on a concave wall. At the onset of curvature there appears a fairly coherent wavelike transverse profile of mean velocity. This disturbance might be interpreted as a kind of large scale Taylor-Goertler type instability superimposed on a conventional turbulent boundary layer; further downstream the coherence degenerates as the turbulence level increases. Boundary-layer profile measurements were made at positions of maxima and minima of transverse profiles of (U-component) mean velocity. The boundary layer at the minima positions is found to be twice as thick as that at the maxima positions. Also, turbulent intensities inside the boundary layer are substantially increased as a result of the concave curvature of the surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Aeronautical Quarterly; 26; Feb. 197
    Format: text
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    A short static-pressure probe design for supersonic flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A static-pressure probe design concept was developed which has the static holes located close to the probe tip and is relatively insensitive to probe angle of attack and circumferential static hole location. Probes were constructed with 10 and 20 deg half-angle cone tips followed by a tangent conic curve section and a tangent cone section of 2, 3, or 3.5 deg, and were tested at Mach numbers of 2.5 and 4.0 and angles of attack up to 12 deg. Experimental results indicate that for stream Mach numbers of 2.5 and 4.0 and probe angle of attack within + or - 10 deg, values of stream static pressure can be determined from probe calibration to within about + or - 4 percent. If the probe is aligned within about 7 deg of the flow experimental results indicated, the stream static pressures can be determined to within 2 percent from probe calibration.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-7978 , L-10033
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    A B-B-G-K-Y framework for fluid turbulence (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A kinetic theory for fluid turbulence is developed from the Liouville equation and the associated BBGKY hierarchy. Real and imaginary parts of Fourier coefficients of fluid variables play the roles of particles. Closure is achieved by the assumption of negligible five-coefficient correlation functions and probability distributions of Fourier coefficients are the basic variables of the theory. An additional approximation leads to a closed-moment description similar to the so-called eddy-damped Markovian approximation. A kinetic equation is derived for which conservation laws and an H-theorem can be rigorously established, the H-theorem implying relaxation of the absolute equilibrium of Kraichnan. The equation can be cast in the Fokker-Planck form, and relaxation times estimated from its friction and diffusion coefficients. An undetermined parameter in the theory is the free decay time for triplet correlations. Some attention is given to the inclusion of viscous damping and external driving forces.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-143101
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    Design and performance of the University of Michigan 6.6-inch hypersonic wind tunnel (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The tunnel described has several design features intended to maintain laminar flow in the boundary layer of its nozzle. Measurements show that transition to turbulence in the nozzle wall boundary layer begins at the throat and is sensitive to surface roughness, heat transfer rate, and longitudinal radius of curvature. The observed dependence of transition on heat transfer rate is the reverse of that predicted by stability theory for infinitesimal disturbances. Tests include boundary layer surveys of a contoured nozzle and a conical nozzle with four interchangeable throats.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2569
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    Induced pressure distribution of a jet in a crossflow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The turbulent flow of a subsonic round jet exhausting perpendicularly from a flat plate into a subsonic crosswind of the same temperature was investigated in the Langley V/STOL tunnel. The large test section of this tunnel made it possible to use a jet with the relatively large diameter of 10.16 cm. Pressures were measured on the flat plate at over 400 locations to provide a detailed description of the static pressure distribution. Results are presented in tabular and graphical forms for jet to crossflow velocity ratios ranging from 2 to 10, and comparisons are made with results of other experiments. The results indicate that the dominant flow parameter affecting the pressure distributions is the ratio of jet to crossflow velocities. The distribution of turbulence on the plate also appears to be a function of velocity ratio.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-7916 , L-9894
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    Metal temperatures and coolant flow in a wire cloth transpiration cooled turbine vane (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental heat transfer investigation was conducted on an air-cooled turbine vane made from wire-wound cloth material and supported by a central strut. Vane temperature data obtained are compared with temperature data from two full-coverage film-cooled vanes made of different laminated construction. Measured porous-airfoil temperatures are compared with predicted temperatures.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-3248 , E-8249
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  • 37
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    Evaluation of T-111 forced-convection loop tested with lithium at 1370 C (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A T-111 alloy (Ta-8% W-2% Hf) forced-convection loop containing molten lithium was operated 3000 hr at a maximum temperature of 1370 C. Flow velocities up to 6.3 m/sec were used, and the results of this forced-convection loop are very similar to those observed in lower velocity thermal-convection loops of T-111 containing lithium. Weight changes were determined at 93 positions around the loop. The maximum dissolution rate occurred at the maximum wall temperature of the loop and was less than 1.3 microns/year. Mass transfer of hafnium, nitrogen, and, to a lesser extent, carbon occurred from the hotter to cooler regions. Exposed surfaces in the highest temperature region were found to be depleted in hafnium to a depth of 60 microns with no detectable change in tungsten content. There was some loss in room-temperature tensile strength for specimens exposed to lithium at 1370 C, attributable to depletion of hafnium and nitrogen and to attendant grain growth.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-134745 , ORNL-TM-4775
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  • 38
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    Nozzle Free Jet Flows Within the Strong Curved Shock Regime (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study based on inviscid analysis was conducted to examine the flow field produced from a convergent-divergent nozzle when a strong curved shock occurs. It was found that a certain constraint is imposed on the flow solution of the problem which is the unique feature of the flow within this flow regime, and provides the reason why the inverse method of calculation cannot be employed for these problems. An approximate method was developed to calculate the flow field, and results were obtained for two-dimensional flows. Analysis and calculations were performed for flows with axial symmetry. It is shown that under certain conditions, the vorticity generated at the jet boundary may become infinite and the viscous effect becomes important. Under other conditions, the asymptotic free jet height as well as the corresponding shock geometry were determined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-142675
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  • 39
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    An experimental documentation of a hypersonic shock-wave turbulent boundary layer interaction flow: With and without separation (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experiment, thoroughly documenting the flow field resulting from the interaction of a shock wave with a nonadiabatic hypersonic turbulent boundary layer, is described. Detailed mean flow and surface data are presented for two shock strengths resulting in attached and separated flows, respectively. The surface measurements include continuous pressure, shear and heat-flux distributions upstream, in, and downstream of the interaction regions. At closely spaced intervals along the surface, boundary-layer profiles of static and pitot pressure and total temperature were obtained from which velocity, density and static temperature profiles were derived. The data are presented in both graphical and tabular form. These data are of sufficient detail to validate advanced computer codes and their associated turbulence models.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-62412 , A-5910
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    Effect of wall edge suction on the performance of a short annular dump diffuser with exit passage flow resistance (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of wall edge suction on the performance of a short annular dump diffuser having a perforated plate flow resistance device in the exit passage was evaluated. Testing was conducted with air at near ambient pressure and temperature at inlet Mach numbers of 0.18 and 0.27 with suction rates up to 13.5 percent. Results show that pressure recovery downstream of the perforated plate was improved significantly by suction. Optimum performance was obtained with the flow resistance plate located at one inlet passage height downstream of the dump plane.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-3221 , E-8149
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    Solution of the equation of heat conduction with time dependent sources: Programmed application to planetary thermal history (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program (Program SPHERE) solving the inhomogeneous equation of heat conduction with radiation boundary condition on a thermally homogeneous sphere is described. The source terms are taken to be exponential functions of the time. Thermal properties are independent of temperature. The solutions are appropriate to studying certain classes of planetary thermal history. Special application to the moon is discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-142546 , JPL-TM-33-718
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    Wind tunnel measurements in the wake of a simple structure in a simulated atmospheric flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measurements of longitudinal mean velocity and turbulence intensity were made in the wake of a rectangular model building in a simulated atmospheric boundary-layer wind. The model building was a 1:50 scale model of a structure used in a wake measurement program at the George C. Marshall Space Flight Center 8-tower boundary-layer facility. The approach wind profile and measurement locations were chosen to match the field site conditions. The wakes of the building in winds from azimuths of 0 and 47 degrees referenced to the normal to the building long axis were examined. The effect of two lines of trees upwind of the building on the wake and the importance of the ratio of the building height to boundary-layer thickness on the extent of the wake were determined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2540 , M-140
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    GASP: A computer code for calculating the thermodynamic and transport properties for ten fluids: Parahydrogen, helium, neon, methane, nitrogen, carbon monoxide, oxygen, fluorine, argon, and carbon dioxide (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A FORTRAN IV subprogram called GASP is discussed which calculates the thermodynamic and transport properties for 10 pure fluids: parahydrogen, helium, neon, methane, nitrogen, carbon monoxide, oxygen, fluorine, argon, and carbon dioxide. The pressure range is generally from 0.1 to 400 atmospheres (to 100 atm for helium and to 1000 atm for hydrogen). The temperature ranges are from the triple point to 300 K for neon; to 500 K for carbon monoxide, oxygen, and fluorine; to 600 K for methane and nitrogen; to 1000 K for argon and carbon dioxide; to 2000 K for hydrogen; and from 6 to 500 K for helium. GASP accepts any two of pressure, temperature and density as input conditions along with pressure, and either entropy or enthalpy. The properties available in any combination as output include temperature, density, pressure, entropy, enthalpy, specific heats, sonic velocity, viscosity, thermal conductivity, and surface tension. The subprogram design is modular so that the user can choose only those subroutines necessary to the calculations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-7808 , E-6501
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    Detailed requirements document for the radiant heat transfer facility post-test data reduction program (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The requirements and functional specifications for a program to process test data obtained by the Radiant Heat Data Acquisition System are defined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-141729 , LEC-5147 , JSC-09403
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  • 45
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    A theoretical method for the analysis and design of axisymmetric bodies (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical method is presented for the computation of the flow field about an axisymmetric body operating in a viscous, incompressible fluid. A potential flow method was used to determine the inviscid flow field and to yield the boundary conditions for the boundary layer solutions. Boundary layer effects in the forces of displacement thickness and empirically modeled separation streamlines are accounted for in subsequent potential flow solutions. This procedure is repeated until the solutions converge. An empirical method was used to determine base drag allowing configuration drag to be computed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2498
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  • 46
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    Analytical comparison of hypersonic flight and wind tunnel viscous/inviscid flow fields (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flow fields were computed about blunted, 0.524 and 0.698 radians, cone configurations to assess the effects of nonequilibrium chemistry on the flow field geometry, boundary layer edge conditions, boundary layer profiles, and heat transfer and skin friction. Analyses were conducted at typical space shuttle entry conditions for both laminar and turbulent boundary layer flow. In these calculations, a wall temperature of 1365 K (2000 F) was assumed. The viscous computer program used in this investigation was a modification of the Blottner non-similar viscous code which incorporated a turbulent eddy viscosity model after Cebeci. The results were compared with equivalent calculations for similar (scaled) configurations at typical wind tunnel conditions. Wind tunnel test gases included air, nitrogen, CF4 and helium. The viscous computer program used for wind tunnel conditions was the Cebeci turbulent non-similar computer code.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2489
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    Patterns of convection in spherical shells (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The problem of the pattern of motion realized in a convectively unstable system with spherical symmetry can be considered without reference to the physical details of the system. Since the solution of the linear problem is degenerate because of the spherical homogeneity, the nonlinear terms must be taken into account in order to remove the degeneracy. The solvability condition leads to the selection of patterns distinguished by their symmetries among spherical harmonics of even order. It is shown that the corresponding convective motions set in as subcritical finite-amplitude instabilities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 72; Nov. 11
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  • 48
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    Finite elements and fluid dynamics (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Difficulties concerning a use of the finite element method in the solution of the nonlinear equations of fluid dynamics are partly related to various 'hidden' instabilities which often arise in fluid calculations. The instabilities are typically due to boundary effects or nonlinearities. It is shown that in certain cases these instabilities can be avoided if certain conservation laws are satisfied, and that the latter are often intimately related to finite elements.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 49
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    Hypersonic ionizing air viscous shock-layer flows over nonanalytic blunt bodies (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The equations which govern the viscous shock-layer flow are presented and the method by which the equations are solved is discussed. The predictions of the present finite-difference method are compared with other numerical predictions as well as with experimental data. The principal emphasis is placed on predictions of the viscous flowfield for the windward plane of symmetry of the space shuttle orbiter and other axisymmetric bodies which approximate the shuttle orbiter geometry. Experimental data on two slender sphere-cones at hypersonic conditions are also considered. The present predictions agreed well with experimental data and with the past predictions. Substantial differences were found between present predictions and more approximate methods.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2550
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  • 50
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    Program and charts for determining shock tube, and expansion tunnel flow quantities for real air (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program in FORTRAN 4 language was written to determine shock tube, expansion tube, and expansion tunnel flow quantities for real-air test gas. This program permits, as input data, a number of possible combinations of flow quantities generally measured during a test. The versatility of the program is enhanced by the inclusion of such effects as a standing or totally reflected shock at the secondary diaphragm, thermochemical-equilibrium flow expansion and frozen flow expansion for the expansion tube and expansion tunnel, attenuation of the flow in traversing the acceleration section of the expansion tube, real air as the acceleration gas, and the effect of wall boundary layer on the acceleration section air flow. Charts which provide a rapid estimation of expansion tube performance prior to a test are included.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-7752 , L-9700
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    Experimental transient turbine blade temperatures in a research engine for gas stream temperatures cycling between 1067 and 1567 k (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental transient turbine blade temperatures were obtained from tests conducted on air-cooled blades in a research turbojet engine, cycling between cruise and idle conditions. Transient data were recorded by a high speed data acquisition system. Temperatures at the same phase of each transient cycle were repeatable between cycles to within 3.9 K (7 F). Turbine inlet pressures were repeatable between cycles to within 0.32 N/sq cm (0.47 psia). The tests were conducted at a gas stream temperature of 1567 K (2360 F) at cruise, and 1067 K (1460 F) at idle conditions. The corresponding gas stream pressures were about 26.2 and 22.4 N/sq cm (38 and 32.5 psia) respectively. The nominal coolant inlet temperature was about 811 K (1000 F).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-71716 , E-8328
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    ERTS-C (Landsat 3) cryogenic heat pipe experiment definition (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight experiment designed to demonstrate current cryogenic heat pipe technology was defined and evaluated. The experiment package developed is specifically configured for flight aboard an ERTS type spacecraft. Two types of heat pipes were included as part of the experiment package: a transporter heat pipe and a thermal diode heat pipe. Each was tested in various operating modes. Performance data obtained from the experiment are applicable to the design of cryogenic systems for detector cooling, including applications where periodic high cooler temperatures are experienced as a result of cyclic energy inputs.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-143797 , BK005-1009
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  • 53
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    Subscale, hydrogen-burning, airframe-integrated-scramjet: Experimental and theoretical evaluation of a water cooled strut airframe-integrated-scramjet: Experimental leading edge (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A water-cooled leading-edge design for an engine/airframe integrated scramjet model strut leading edge was evaluated. The cooling design employs a copper cooling tube brazed just downstream of the leading edge of a wedge-shaped strut which is constructed of oxygen-free copper. The survival of the strut leading edge during a series of tests at stagnation point heating rates confirms the practicality of the cooling design. A finite difference thermal model of the strut was also proven valid by the reasonable agreement of calculated and measured values of surface temperature and cooling-water heat transfer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-72682
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    A users manual for a revised version of the Langley charring ablator program (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program is described that will compute the transient response of a thermal protection material to a prescribed heat input at the surface. The program has the capability of analyzing pyrolysis gas chemical kinetics in detail and treating pyrolysis reactions-in-depth. Deposition of solid products produced by chemical reactions in the gas phase is included in the analysis. An outline is given for the theory. detailed operating instructions for the computer program are included.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-72677
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    Criteria for underground heat distribution systems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Underground heat distribution system design and evaluation criteria are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-148514 , TR-66
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  • 56
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    The NATA code; theory and analysis. Volume 3: Programmer's manual (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The present, third volume of the final report is a programmer's manual for the code. It provides a listing of the FORTRAN 4 source program; a complete glossary of FORTRAN symbols; a discussion of the purpose and method of operation of each subroutine (including mathematical analyses of special algorithms); and a discussion of the operation of the code on IBM/360 and UNIVAC 1108 systems, including required control cards and the overlay structure used to accommodate the code to the limited core size of the 1108. In addition, similar information is provided to document the programming of the NOZFIT code, which is employed to set up nozzle profile curvefits for use in NATA.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-141744 , AVSD-0138-75-RR-VOL-3
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    Development of an efficient computer code to solve the time-dependent Navier-Stokes equations (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A research effort was conducted with the goal of reducing computer time of a Navier Stokes Computer Code for prediction of viscous flow fields about lifting bodies. A two-dimensional, time-dependent, laminar, transonic computer code (STOKES) was modified to incorporate a non-uniform timestep procedure. The non-uniform time-step requires updating of a zone only as often as required by its own stability criteria or that of its immediate neighbors. In the uniform timestep scheme each zone is updated as often as required by the least stable zone of the finite difference mesh. Because of less frequent update of program variables it was expected that the nonuniform timestep would result in a reduction of execution time by a factor of five to ten. Available funding was exhausted prior to successful demonstration of the benefits to be derived from the non-uniform time-step method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-137851 , SR-26
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  • 58
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    The NATA code; theory and analysis. Volume 2: User's manual (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The NATA code is a computer program for calculating quasi-one-dimensional gas flow in axisymmetric nozzles and rectangular channels, primarily to describe conditions in electric archeated wind tunnels. The program provides solutions based on frozen chemistry, chemical equilibrium, and nonequilibrium flow with finite reaction rates. The shear and heat flux on the nozzle wall are calculated and boundary layer displacement effects on the inviscid flow are taken into account. The program contains compiled-in thermochemical, chemical kinetic and transport cross section data for high-temperature air, CO2-N2-Ar mixtures, helium, and argon. It calculates stagnation conditions on axisymmetric or two-dimensional models and conditions on the flat surface of a blunt wedge. Included in the report are: definitions of the inputs and outputs; precoded data on gas models, reactions, thermodynamic and transport properties of species, and nozzle geometries; explanations of diagnostic outputs and code abort conditions; test problems; and a user's manual for an auxiliary program (NOZFIT) used to set up analytical curvefits to nozzle profiles.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-141743 , AVSD-0068-75-CR-VOL-2
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    Mean flow characteristics for the oblique impingement of an axisymmetric jet (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The oblique impingement of an axisymmetric jet has been investigated. A summary of the data and the analytical interpretations of the dominant mechanisms which influence the flow are reported. The major characteristics of the shallow angle oblique jet impingement flow field are: (1) minimal dynamic spreading as revealed by the surface pressure field, (2) pronounced kinematic spreading as revealed by the jet flow velocity field, (3) a pronounced upstream shift of the stagnation point from the maximum pressure point, (4) the production of streamwise vorticity by the impingement process.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146856
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    Fluid flow electrophoresis in space (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Four areas relating to free-flow electrophoresis in space were investigated. The first was the degree of improvement over earthbound operations that might be expected. The second area of investigation covered the problems in developing a flowing buffer electrophoresis apparatus. The third area of investigation was the problem of testing on the ground equipment designed for use in space. The fourth area of investigation was the improvement to be expected in space for purification of biologicals. The results of some ground-based experiments are described. Other studies included cooling requirements in space, fluid sealing techniques, and measurement of voltage drop across membranes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-144218
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    Mean flow field and surface heating produced by unequal shock interactions at hypersonic speeds (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mean velocity profiles were measured in a free shear layer produced by the interaction of two unequal strength shock waves at hypersonic free-stream Mach numbers. Measurements were made over a unit Reynolds number range of 3,770,000 per meter to 17,400,000 per meter based on the flow on the high velocity side of the shear layer. The variation in measured spreading parameters with Mach number for the fully developed flows is consistent with the trend of the available zero velocity ratio data when the Mach numbers for the data given in this study are taken to be characteristic Mach numbers based on the velocity difference across the mixing layer. Surface measurements in the shear-layer attachment region of the blunt-body model indicate peak local heating and static pressure consistent with other published data. Transition Reynolds numbers were found to be significantly lower than those found in previous data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8092 , L-10444
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  • 62
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    Analysis of liquid-metal-jet impingement cooling in a corner region and for a row of jets (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A conformal mapping method was used to analyze liquid-metal-jet impingement heat transfer. The jet flow region and energy equation are transformed to correspond to uniform flow in a parallel plate channel with nonuniform heat addition along a portion of one wall. The exact solution for the wall-temperature distribution was obtained in the transformed channel, and the results are mapped back into the physical plane. Two geometries are analyzed. One is for a single slot jet directed either into an interior corner formed by two flat plates, or over the external sides of the corner; the flat plates are uniformly heated, and the corner can have various included angles. The heat-transfer coefficient at the stagnation point at the apex of the plates is obtained as a function of the corner angle, and temperature distributions are calculated along the heated walls. The second geometry is an infinite row of uniformly spaced parallel slot jets impinging normally against a uniformly heated plate. The heat-transfer behavior is obtained as a function of the spacing between the jets. Results are given for several jet Peclet numbers from 5 to 50.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8096 , E-8325
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  • 63
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    Boundary-layer theory for blast waves (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: It is profitable to consider the blast wave as a flow field consisting of two regions: the outer, which retains the properties of the inviscid solution, and the inner, which is governed by flow equations including terms expressing the effects of heat transfer and, concomitantly, viscosity. The latter region thus plays the role of a boundary layer. Reported here is an analytical method developed for the study of such layers, based on the matched asymptotic expansion technique combined with patched solutions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 71; Sept. 9
    Format: text
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  • 64
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    Pressure- and buoyancy-driven thermal convection in a rectangular enclosure (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Results are presented for unsteady laminar thermal convection in compressible fluids at various reduced levels of gravity in a rectangular enclosure which is heated on one side and cooled on the opposite side. The results were obtained by solving numerically the equations of conservation for a viscous, compressible, heat-conducting, ideal gas in the presence of a gravitational body force. The formulation differs from the Boussinesq simplification in that the effects of variable density are completely retained. A conservative, explicit, time-dependent, finite-difference technique was used and good agreement was found for the limited cases where direct comparison with previous investigations was possible. The solutions show that the thermally induced motion is acoustic in nature at low levels of gravity and that the unsteady-state rate of heat transfer is thereby greatly enhanced relative to pure conduction. The nonlinear variable density profile skews the streamlines towards the cooler walls but is shown to have little effect on the steady-state isotherms.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 70; Aug. 26
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  • 65
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    Turbulent flow between a rotating disk and a parallel wall (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A scalar effective viscosity method is used to calculate the incompressible flow in the gap between two infinite, parallel smooth disks, one of them rotating and the other stationary. The flow is calculated for two values of the gap Reynolds number omega(s squared)/nu, namely 296 and 2852, where omega is the disk angular velocity, s the gap width, and nu the kinematic viscosity of the fluid; and over a range of radial Reynolds number omega(r squared)/nu from 0 to 10 million, where r is the radius from the axis of rotation. A numerical shooting technique is used to match the two boundary-layer flows arising on the disk and wall. Gradual transition is assumed for radial Reynolds numbers from 160,000 to 250,000. The results are in good agreement with Daily and Nece's measurements of velocity profiles and disk friction drag for enclosed rotating disks, and at sufficiently large radius the local skin friction approaches that of turbulent Couette flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; May 1975
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  • 66
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    A Method for Calculating the Induced Pressure Distribution Associated with a Jet in a Crossflow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A model is presented which can be used to study the loss of lift during hovering and horizontal flight of the VTOL aircraft. The model numerically predicts the pressure distribution induced by a round, turbulent, unheated, subsonic jet exhausting normally through a flat plate into a subsonic crossflow. The complete model assumes that the predominant features of the flow are jet entrainment and a pair of contrarotating vortices which form downstream of the jet. Experimentally determined vortex properties and a reasonable assumption concerning jet entrainment were used. Potential flow considerations were used except in the wake region, where a simple method for approximating the pressure distribution was suggested. The calculated pressure distribution, lift, and pitching moments on the flat plate are presented for a jet to crossflow velocity ratio of 8 and were compared with experimental results. A computer program is given which was used to calculate the pressure distribution across the flat plate.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146434
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  • 67
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    Flutter of articulated pipes at finite amplitude (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Previous studies of the behavior of pipes conveying fluid have assumed that the fluid velocity relative to the pipe is a known quantity and is unaffected by the motion of the pipe. This approach eliminates the need to find the flow equations of motion, and is adequate for infinitesimal transverse amplitudes of motion of the pipe system, but is incapable of predicting what will be the effect of larger amplitudes. This last shortcoming may be of importance when flow velocities are near critical velocities, that is, velocities at which the system begins to flutter. It is the purpose of the present study to investigate in greater detail the dynamic behavior of pipes in the vicinity of critical velocities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146669 , AD-A017634 , SUDAM-75-9 , AFOSR-75-1520TR
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  • 68
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    High subsonic flow tests of a parallel pipe followed by a large area ratio diffuser (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were performed on a pilot model duct system in order to explore its aerodynamic characteristics. The model was scaled from a design projected for the high speed operation mode of the Aircraft Noise Reduction Laboratory. The test results show that the model performed satisfactorily and therefore the projected design will most likely meet the specifications.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-144955 , TR-75-T13
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  • 69
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    A numerical scheme to solve unstable boundary value problems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new iterative scheme for solving boundary value problems is presented. It consists of the introduction of an artificial time dependence into a modified version of the system of equations. Then explicit forward integrations in time are followed by explicit integrations backwards in time. The method converges under much more general conditions than schemes based in forward time integrations (false transient schemes). In particular it can attain a steady state solution of an elliptical system of equations even if the solution is unstable, in which case other iterative schemes fail to converge. The simplicity of its use makes it attractive for solving large systems of nonlinear equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146552
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  • 70
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    Wall-wake velocity profile for compressible non-adiabatic flows (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A form of the wall-wake profile, which is applicable to flows with heat transfer, and for which a variation in y = O at y = delta, was suggested. The modified profile, which takes into account the effect of turbulent Prandtl number, was found to provide a good representation of experimental data for a wide range numbers and heat transfer. The Cf values which are determined by a least squares fit of the profile to the data agree well with values which were measured by the floating element technique. In addition, the values of delta determined by the fit correspond more closely to the outer edge of the viscous flow region than those obtained with earlier versions of the wall-wake profile.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146393
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  • 71
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    Studies of heat source driven natural convection (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Natural convection energy transport in a horizontal layer of internally heated fluid was measured for Rayleigh numbers from 1890 to 2.17 x 10 to the 12th power. The fluid layer is bounded below by a rigid zero-heat-flux surface and above by a rigid constant-temperature surface. Joule heating by an alternating current passing horizontally through the layer provides the uniform volumetric energy source. The overall steady-state heat transfer coefficient at the upper surface was determined by measuring the temperature difference across the layer and power input to the fluid. The correlation between the Nusselt and Rayleigh numbers for the data of the present study and the data of the Kulacki study is given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146395 , TR-3746-2
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  • 72
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    Parametric performance of circumferentially grooved heat pipes with homogeneous and graded-porosity slab wicks at cryogenic temperatures (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A recently developed, potentially high-performance nonarterial wick has been extensively tested. This slab wick has an axially varying porosity which can be tailored to match the local stress imposed on the wick. The purpose of the tests was to establish the usefulness of the graded-porosity slab wick at cryogenic temperatures between 110 K and 260 K, with methane and ethane as working fluids. For comparison, a homogeneous (i.e., uniform porosity) slab wick was also tested. The tests included: (1) maximum heat pipe performance as a function of fluid inventory, (2) maximum performance as a function of operating temperature, (3) maximum performance as a function of evaporator elevation, and (4) influence of slab wick orientation on performance. The experimental data was compared with theoretical predictions obtained with the computer program GRADE.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-73095 , A-6405
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  • 73
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    Heat-flux gage measurements on a flat plate at a Mach number of 4.6 in the VSD high speed wind tunnel, a feasibility test (LA28) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of employing thin-film heat-flux gages was studied as a method of defining boundary layer characteristics at supersonic speeds in a high speed blowdown wind tunnel. Flow visualization techniques (using oil) were employed. Tabulated data (computer printouts), a test facility description, and photographs of test equipment are given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-144582 , DMS-DR-2280
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  • 74
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    Incident shock-wave characteristics in air, argon, carbon dioxide, and helium in a shock tube with unheated helium driver (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Incident shock-wave velocities were measured in the Langley 6-inch expansion tube, operated as a shock tube, with air, argon, carbon dioxide, and helium as test gases. Unheated helium was used as the driver gas and most data were obtained at pressures of approximately 34 and 54 MN/sq m. A range of pressure ratio across the diaphragm was obtained by varying the quiescent test-gas pressure, for a given driver pressure, from 0.0276 to 34.5 kN/sq m. Single- and double-diaphragm modes of operation were employed and diaphragms of various materials tested. Shock velocity was determined from microwave interferometer measurements, response of pressure transducers positioned along interferometer measurements, response of pressure transducers positioned along the driven section (time-of-arrival gages), and to a lesser extent, measured tube-wall pressure. Velocities obtained from these methods are compared and limitations of the methods discussed. The present results are compared with theory and the effects of diaphragm mode (single or double diaphragm), diaphragm material, heating of the driver gas upon pressurization of the driver section, diaphragm opening time, interface mixing, and two-dimensional (nonplanar) flow are discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8099 , L-10520
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  • 75
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    A finite-difference analysis of the nozzle starting process in an expansion tunnel (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A suitable finite-difference method for computing the quasi-one-dimensional unsteady flow in an expansion tunnel nozzle was identified. The difference equations are presented along with the appropriate stability limits. A parametric study of the starting process in an expansion tunnel nozzle is made, and acceptable operating conditions were determined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8105 , L-10500
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  • 76
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    Analysis of a heat transfer device for measuring film coefficients (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat transfer device consisting of a heated rotating cylinder in a bath was analyzed for its effectiveness to determine heat transfer coefficient of fluids. A time dependent analysis shows that the performance is insensitive to the value of heat transfer coefficient with the given rig configuration.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-71809 , E-8156
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  • 77
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    Buoyant and capillary natural convection in infinite horizontal liquid layers heated laterally (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Solutions are presented for the equations describing natural convection in a planar, horizontal layer of liquid with a constant, linear temperature gradient along the unbounded top and bottom surfaces. Both buoyancy and capillary forces are considered to drive thermal convection. The results are compared to earlier analyses for bounded liquid layers and then applied to containerless metal melts undergoing solidification in the microgravity environment of near-earth orbit.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Letters in Heat and Mass Transfer; 2; May-June
    Format: text
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  • 78
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    Stagnation-point heat transfer correlation for ionized gases (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Based on previous laminar boundary-layer solutions for argon, xenon, nitrogen, and air, it is shown that the effect of gas ionization on stagnation-point heat transfer can be correlated with the variation of the frozen Prandtl number across the boundary layer. A formula is obtained for stagnation-point heat transfer in a noble gas and is shown to be valid from the low-temperature range to the region of strong ionization. It is concluded that the considered effect can be well correlated by the 0.7 power of the Prandtl-number ratio across the boundary layer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 18; Aug. 197
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  • 79
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    Experimental results for the transpired turbulent boundary layer in an adverse pressure gradient (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The fluid mechanics of transpired incompressible turbulent boundary layers under zero and adverse pressure gradient conditions is investigated using an open-ended wind tunnel with a porous floor in the test section and a secondary air system for supply and metering of the transpiration air. All velocity profiles and turbulence profiles are obtained by linearized constant-temperature hot-wire anemometry. The wall shear stress is determined by measuring the shear stress away from the wall and extrapolating to the wall by integrating the boundary layer equations for the shear-stress profile. Equilibrium boundary layers are obtained when the transpiration velocity is varied such that the blowing parameter and the Clauser pressure gradient parameter are held constant. The experimental results obtained are presented in tabular and graphical forms.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 69; May 27
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  • 80
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    Form of the turbulence dissipation equation as applied to curved and rotating turbulent flows (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An exact turbulence dissipation equation in the generalized relative system is presented. Simplified forms of the equation are obtained for computational purposes in the high Reynolds number approximation. Modeling of the rotation term is proposed. Modeling of the other higher-order terms is also presented in a generalized system using the tensor invariance technique. An estimate of the angular velocity is provided for the rotation term to be included in the turbulence dissipation equation. The associated significant curvature terms for turbomachinery flows are also identified.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 18; Oct. 197
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  • 81
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    Numerical calculation of the internal flow field in a centrifugal compressor impeller (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An iterative numerical method has been developed for the calculation of steady, three-dimensional, viscous, compressible flow fields in centrifugal compressor impellers. The computer code, which embodies the method, solves the steady three dimensional, compressible Navier-Stokes equations in rotating, curvilinear coordinates. The solution takes place on blade-to-blade surfaces of revolution which move from the hub to the shroud during each iteration.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-134984 , SR-27
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  • 82
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    A comparison of measured and predicted test flow in an expansion tube with air and oxygen test gases (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simultaneous time-resolved measurements of temperature, density, pitot pressure, and wall pressure in both air and O2 test gases were obtained in the Langley pilot model expansion tube. These tests show nonequilibrium chemical and vibrational relaxation significantly affect the test-flow condition. The use of an electromagnetic device to preopen the secondary diaphragm before the arrival of the primary shock wave resulted in an improvement in the agreement between the measured pitot pressure and the value inferred from measured density and interface velocity. Boundary-layer splitter plates used to reduce the wall boundary layer show that this disagreement in the measured and inferred pitot pressures is not a result of boundary-layer effects.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8068 , L-10356
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  • 83
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    Inviscid transonic flow computations with shock fitting (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: First-and second-order numerical procedures are presented for calculating two-dimensional transonic flows that treat shock waves as discontinuities. Their application to a simple but nontrivial problem for which there are limited theoretical results is discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145430
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  • 84
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    Viscous shock layer solutions for turbulent flow of radiating gas mixtures in chemical equilibrium (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The viscous shock layer equations for hypersonic laminar and turbulent flows of radiating or nonradiating gas mixtures in chemical equilibrium are presented for two-dimensional and axially symmetric flow fields. Solutions are obtained using an implicit finite difference scheme and results are presented for hypersonic flow over spherically blunted cone configurations at free stream conditions representative of entry into the atmosphere of Venus. These data are compared with solutions obtained using other methods of analysis.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-72764 , TR-75-T9
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  • 85
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    Hot wire anemometry in transonic flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of hot-wire anemometry for obtaining fluctuating data in transonic flows has been evaluated. From hot-wire heat loss correlations based on previous transonic data, the sensitivity coefficients for velocity, density, and total temperature fluctuations have been calculated for a wide range of test conditions and sensor parameters. For sensor Reynolds numbers greater than 20 and high sensor overheat ratios, the velocity sensitivity remains independent of Mach number and equal to the density sensitivity. These conclusions were verified by comparisons of predicted sensitivities with those from recent direct calibrations in transonic flows. Based on these results, techniques are presented to obtain meaningful measurements of fluctuating velocity, density, and Reynolds shear stress using hot-wire and hot-film anemometers. Examples of these measurements are presented for two transonic boundary layers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-62495 , A-6309
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  • 86
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    Vapor-modulated heat pipe report. Flight data analysis and further development of variable-conductance heat pipes (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and testing of a heat pipe for spacecraft application is presented. The application in mind calls for heat loads up to 20 watts, a set-point temperature of 294K, and a sink that varies from -220K to nearly as high as the set-point. The overall heat pipe length is 137 cm. Two basically different mechanisms of achieving variable conductance in the pipe by vapor-flow throttling were studied. In one, the thermal resistance between the heat source and sink is due to a saturation-temperature drop corresponding to the vapor-pressure drop developed across the valve. In the other, the pressure difference across the valve induces capillary groove and wick dry out in an evaporation region, and thus results in an increased thermal resistance. This mechanism was selected for fabrication and testing. The pipe is a stainless-steel/methanol two-heat-pipe system. Results are presented and discussed. Engineering drawings and specifications of the pipe are shown.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-146143 , TRW-26263-6015-RU-00
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  • 87
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    An effective solution to the nonlinear, nonstationary Navier-Stokes equations for two dimensions (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A sequence of approximate solutions for the nonlinear, nonstationary Navier-Stokes equations for a two-dimensional domain, from which explicit error estimates and rates of convergence are obtained, is described. This sequence of approximate solutions is based primarily on the Newton-Kantorovich method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-62493 , A-6294
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  • 88
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    A comparison of measured and predicted sphere shock shapes in hypersonic flows with density ratios from 4 to 19 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measured shock shapes are presented for sphere and hemisphere models in helium, air, CF4, C2F6, and CO2 test gases, corresponding to normal-shock density ratios (primary factor governing shock detachment distance of blunt bodies at hypersonic speeds) from 4 to 19. These shock shapes were obtained in three facilities capable of generating the high density ratios experienced during planetary entry at hypersonic conditions; namely, the 6-inch expansion tube, with hypersonic CF4 tunnel, and pilot CF4 Mach 6 tunnel (with CF4 replaced by C2F6). Measured results are compared with several inviscid perfect-gas shock shape predictions, in which an effective ratio of specific heats is used as input, and with real-gas predictions which include effects of a laminar viscous layer and thermochemical nonequilibrium.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8076 , L-10445
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  • 89
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    A family of approximate solutions and explicit error estimates for the nonlinear stationary Navier-Stokes problem (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An algorithm for solving the nonlinear stationary Navier-Stokes problem is developed. Explicit error estimates are given. This mathematical technique is potentially adaptable to the separation problem.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-62497 , A-6319
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  • 90
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    A wall-wake velocity profile for turbulent compressible boundary layers with heat transfer (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A modified form of the wall-wake profile which is applicable to flows with heat transfer is presented. The modified profile takes into account the effect of a turbulent Prandtl number; it was found to provide a good representation of the experimental data from several sources. The C sub f values which are determined by a least squares fit of the profile to the data agree well with values which were measured by the floating element technique.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-119131
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  • 91
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    A tabulation of pipe length to diameter ratios as a function of Mach number and pressure ratios for compressible flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer programs and resulting tabulations are presented of pipeline length-to-diameter ratios as a function of Mach number and pressure ratios for compressible flow. The tabulations are applicable to air, nitrogen, oxygen, and hydrogen for compressible isothermal flow with friction and compressible adiabatic flow with friction. Also included are equations for the determination of weight flow. The tabulations presented cover a wider range of Mach numbers for choked, adiabatic flow than available from commonly used engineering literature. Additional information presented, but which is not available from this literature, is unchoked, adiabatic flow over a wide range of Mach numbers, and choked and unchoked, isothermal flow for a wide range of Mach numbers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-72756
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  • 92
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    Theoretical face pressure and drag characteristics of forward-facing steps in supersonic turbulent boundary layers (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical investigation of the pressure distributions and drag characteristics was made for forward facing steps in turbulent flow at supersonic speeds. An approximate solution technique proposed by Uebelhack has been modified and extended to obtain a more consistent numerical procedure. A comparison of theoretical calculations with experimental data generally indicated good agreement over the experimentally available range of ratios of step height to boundary layer thickness from 7 to 0.05.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8040 , L-10331
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  • 93
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    Turbulent wall jet in a coflowing stream (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical investigation was undertaken to develop a relatively simple model of a two-dimensional, turbulent wall jet in a coflowing stream. The incompressible jet flow was modeled by using an integral method which includes turbulent shear stress, entrainment, and heat transfer. The method solves the conservation equations for the average jet flow properties and uses the velocity profile suggested by Escudier and Nicoll to obtain detailed characteristics of the jet on a flat plate. The analytical results compare favorably with experimental data for a range of injection velocities, which demonstrates the usefulness of the theory for estimating jet growth, velocity decay, and wall skin friction. The theory, which was applied to a Coanda jet on a circular cylinder, provided estimates of suction pressures aft of the jet exit that were in close agreement with experimental values.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TN-D-8025 , L-10260
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  • 94
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    Jet pump assisted artery (1975)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A procedure for priming an arterial heat pump is reported; the procedure also has a means for maintaining the pump in a primed state. This concept utilizes a capillary driven jet pump to create the necessary suction to fill the artery. Basically, the jet pump consists of a venturi or nozzle-diffuser type constriction in the vapor passage. The throat of this venturi is connected to the artery. Thus vapor, gas, liquid, or a combination of the above is pumped continuously out of the artery. As a result, the artery is always filled with liquid and an adequate supply of working fluid is provided to the evaporator of the heat pipe.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-137778 , DTM-75-6
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  • 95
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    Aerodynamic heating to the gaps and surfaces of simulated reusable-surface-insulation tile arrays in turbulent flow at Mach 6.6 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made on a simulated reusable-surface-insulation tile array in a turbulent boundary layer to determine aerodynamic-heating distributions representative of those expected on the surface of the shuttle orbiter during earth entry due to the presence of longitudinal and transverse surface gaps. The tests were conducted in an 8-foot high-temperature structures tunnel in a test medium of methane-air combustion products at a nominal Mach number of 6.6 and over a free-stream Reynolds number range from 2,000,000 to 4,900,000 per meter (600,000 to 1,500,000 per foot). The results were used to assess the aerodynamic heating effects produced by parameters that include gap width, boundary-layer displacement thickness, in-line and staggered tile arrangement, and tile protrusion.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-3225 , L-10188
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  • 96
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    Finite element computation of a viscous compressible free shear flow governed by the time dependent Navier-Stokes equations (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A finite element algorithm for solution of fluid flow problems characterized by the two-dimensional compressible Navier-Stokes equations was developed. The program is intended for viscous compressible high speed flow; hence, primitive variables are utilized. The physical solution was approximated by trial functions which at a fixed time are piecewise cubic on triangular elements. The Galerkin technique was employed to determine the finite-element model equations. A leapfrog time integration is used for marching asymptotically from initial to steady state, with iterated integrals evaluated by numerical quadratures. The nonsymmetric linear systems of equations governing time transition from step-to-step are solved using a rather economical block iterative triangular decomposition scheme. The concept was applied to the numerical computation of a free shear flow. Numerical results of the finite-element method are in excellent agreement with those obtained from a finite difference solution of the same problem.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-72894
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  • 97
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    On the development of noise-producing large-scale wavelike eddies in a plane turbulent jet (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper studies the development of large-scale wavelike eddies in a two-dimensional turbulent jet, extending earlier work on the mixing region (Liu, 1974). The basic mean flow developes from one of mixing-region type with an initially specified boundary-layer thickness into a fully developed jet. This study brings out the role of the varicose and sinuous modes as they develop in a growing mean flow. In general, it is found that, for a given frequency parameter, the varicose mode has a shorter streamwise lifetime than the sinuous mode. For lower frequencies, the latter persists past the end of the potential core only to become subject to dissipation by the enhanced fine-scale turbulent activity in that region.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 70; July 29
    Format: text
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  • 98
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    Interaction between a shock wave and a turbulent boundary layer in transonic flow (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Interaction between a shock wave and an unseparated turbulent boundary layer is considered. The method of matched asymptotic expansions is used, with solutions valid in the double limit as Reynolds number tends to infinity and Mach number tends to unity. The shock is weak enough that interaction effects can be considered as perturbations to the undisturbed flow; the case considered is that where the sonic line is near the outer edge of the boundary layer. It is shown that, with order estimates for Reynolds stress perturbations, the induced wall pressure distribution can be calculated using only the two outer interaction regions, independent of a specific closure condition and that this solution is in fact a turbulent free interaction solution. A detailed analysis of the inner regions, for which an eddy viscosity model for the Reynolds shear stress is used, provides a description of the variations in velocity, temperature and density near and at the wall.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: SIAM Journal on Applied Mathematics; 29; July 197
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  • 99
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    Modal equations for cellular convection (1975)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: We expand the fluctuating flow variables of Boussinesq convection in the planform functions of linear theory. Our proposal is to consider a drastic truncation of this expansion as a possible useful approximation scheme for studying cellular convection. With just one term included, we obtain a fairly simple set of equations which reproduces some of the qualitative properties of cellular convection and whose steady-state form has already been derived by Roberts (1966). This set of 'modal equations' is analyzed at slightly supercritical and at very high Rayleigh numbers. In the latter regime the Nusselt number varies with Rayleigh number just as in the mean-field approximation with one horizontal scale when the boundaries are rigid. However, the Nusselt number now depends also on the Prandtl number in a way that seems compatible with experiment. The chief difficulty with the approach is the absence of a deductive scheme for deciding which planforms should be retained in the truncated expansion.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 68; Apr. 29
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  • 100
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    Unified nonlinear approach to both weak and strong-interaction problems (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The numerical results are obtained for heat transfer, skin-friction, and viscous interaction induced pressure for a step-wise accelerated flat plate in hypersonic flow. In the unified approach here the results are presented for both weak and strong-interaction problems without employing any linearization scheme. With the help of the numerical method used in this work an accurate prediction of wall shear can be made for the problems with plate velocity changes of 1% or larger. The obtained results indicate that the transient contribution to the induced pressure for helium is greater than that for air.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Acta Mechanica; 21; 1-2,; 1975
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