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  • Inorganic Chemistry  (765)
  • FLUID MECHANICS AND HEAT TRANSFER
  • 2015-2019
  • 1990-1994
  • 1975-1979  (989)
  • 1978  (989)
Collection
Keywords
Publisher
Years
  • 2015-2019
  • 1990-1994
  • 1975-1979  (989)
Year
  • 1
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    Application of fluidics to new control components (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: The inherent tolerance for nuclear radiation makes fluidic devices candidates for nuclear rocket control systems. Also, they are being considered for supersonic jet engine inlet control because of their high temperature and vibration tolerance. Three new control components being considered for these applications are described. A fluidic circuit to control a pneumatic stepping motor for nuclear rocket control drum actuation is discussed. An all-fluidic sensor being developed for determining the position of the normal shock in the inlet of a supersonic jet engine is outlined. A new vortex valve configuration is developed to prevent supersonic jet engine inlet unstarts by regulating bypass flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 365-386
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  • 2
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    Characteristics of the unsteady motion on transversely sheared mean flows (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: An explicit representation for the unsteady motion on a transversely sheared mean flow is obtained which corresponds to the gustline motion on a uniform mean flow. The important features of this motion are discussed. It is shown that its velocity, pressure and vorticity are all induced by a certain disturbance field that is a linear combination of the vorticity and particle-displacement fields and is everywhere frozen in the mean flow. The general ideas are illustrated by considering the scattering of a gust by a half-plane embedded in a shear flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 84; Jan. 30
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  • 3
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    Critical issues in viscous flow computations (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In developing computer programs to numerically solve the Navier-Stokes equations, the purpose of the computation must be clearly kept in mind. In the Air Force, the purpose is to provide design information on non-linear aerodynamic phenomenon for aircraft that perform throughout the flight corridor. This translates into the requirement for a computer program which can solve the time averaged compressible Navier-Stokes equations (with a turbulence model) in three dimensions for generalized geometries. The intended application of the results then controls the priorities in addressing critical issues. Recurrent problem areas encountered in the study of viscous flow include: (1) grid generation for arbitrary geometry; (2) numerical difficulties; (3) turbulence models; (4) accuracy and efficiency; and (5) smearing of discontinuities.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 168-175
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  • 4
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    Computational requirements for three-dimensional flows (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The computational requirements needed for predicting steady viscous flow over complex configurations are considered. The desired predictions must be made at reasonable expense, require a reasonable amount of storage space, and result in solutions that are sufficiently accurate. The data needed to estimate the cost of Navier-Stokes solutions is not available; therefore, experience with the solution of the three-dimensional boundary layers equations are used to illustrate the needed information and what can be expected for the Navier-Stokes solutions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 145-153
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  • 5
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    A dual assault upon turbulence (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: All known calculation methods incorporate some sort of turbulence model to reduce the infinite hierarchy of equations, under Reynolds' averaging, to a finite set. All such models suffer from a certain ad hoc nature. A dual structure model was developed wherein the turbulence field is, somewhat arbitrarily, decomposed into large eddies which presumably are dominant contributors to the Reynolds' stress and small eddies which feed on the large eddies as these, in turn feed upon the average flow to gain their energy. These concepts have been developed into a dual approach, one extractive and the other predictive as outlined below.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 260-266
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  • 6
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    Computing viscous flows (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Although the goals and techniques of computational aerodynamics and computational fluid dynamics differ, advancement in the physical and mathematical aspects of the latter are required for progress in aerodynamic computation. The most attractive approach is the use of hybrid methods where both the equations treated and the solution algorithms reflect the local character of the flow. A working general turbulence model that is only peripherally related to the availability of large fast computers would provide a significant breakthrough in computational aerodynamics. There is no unanimity of opinion as to what may be the optimum algorithm or family of algorithms in the next decade. While it is premature to develop an optimum processor, such a machine dedicated to study the structure of solutions to the three-dimensional time-dependent Navier-Stokes equations and to the computability of turbulence would be very valuable.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Future Computer Requirements for Computational Aerodynamics; p 209-220
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  • 7
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    Viscous flow simulation requirements (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Although significant advances have been made in the simulation of two-dimensional compressible laminar viscous flows by numerically solving the compressible Navier-Stokes (N.S.) equations, problem areas still remain to be solved before viscous flows requiring solution of the compressible N.S. equations can be efficiently and accurately simulated for flows of aerodynamic interest. These problem areas include turbulence (three-dimensional character), complex geometry, flow unsteadiness, placement of artificial boundaries relative to solid boundaries, specification of boundary conditions, and large flow gradients near surfaces and in the vicinity of shock waves for supersonic flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 176-208
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  • 8
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    Computational Fluid Dynamics (CFD): Future role and requirements as viewed by an applied aerodynamicist (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The problem of designing the wing-fuselage configuration of an advanced transonic commercial airliner and the optimization of a supercruiser fighter are sketched, pointing out the essential fluid mechanical phenomena that play an important role. Such problems suggest that for a numerical method to be useful, it must be able to treat highly three dimensional turbulent separations, flows with jet engine exhausts, and complex vehicle configurations. Weaknesses of the two principal tools of the aerodynamicist, the wind tunnel and the computer, suggest a complementing combined use of these tools, which is illustrated by the case of the transonic wing-fuselage design. The anticipated difficulties in developing an adequate turbulent transport model suggest that such an approach may have to suffice for an extended period. On a longer term, experimentation of turbulent transport in meaningful cases must be intensified to provide a data base for both modeling and theory validation purposes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 132-142
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  • 9
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    A numerical study of capillary stability in a circular cylindrical container with a concave spheroidal bottom (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper describes a theoretical investigation of the stability under gravitational and surface forces of a liquid in a circular cylindrical container with a concave spheroidal bottom for the case in which the volume of the liquid is sufficiently small so that the bottom is not covered completely. The gravitational field is assumed to be directed along the symmetry axis of the container, and for a specific container shape the critical Bond number is calculated as a function of liquid volume for contact angles of gamma = 0, 1, 2, and 4 deg. For gamma = 0 deg, some critical equilibrium configurations and corresponding perturbation modes are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Computer Methods in Applied Mechanics and Engineering; 16; Dec. 197
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  • 10
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    A comparison of the Method of Lines to finite difference techniques in solving time-dependent partial differential equations (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Steady state solutions to two time dependent partial differential systems have been obtained by the Method of Lines (MOL) and compared to those obtained by efficient standard finite difference methods: (1) Burger's equation over a finite space domain by a forward time central space explicit method, and (2) the stream function - vorticity form of viscous incompressible fluid flow in a square cavity by an alternating direction implicit (ADI) method. The standard techniques were far more computationally efficient when applicable. In the second example, converged solutions at very high Reynolds numbers were obtained by MOL, whereas solution by ADI was either unattainable or impractical. With regard to 'set up' time, solution by MOL is an attractive alternative to techniques with complicated algorithms, as much of the programming difficulty is eliminated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Computers and Fluids; 6; June 197
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  • 11
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    Experimental temperature distribution and heat load characteristics of rotating heat pipes (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Experimental results show conclusively that the presence of a small quantity of a noncondensable gas (NCG) mixed with the working fluid has a considerable effect on the condensation process in a rotating heat pipe. The temperature distribution in the condenser shows the blanketing effect of the NCG and the ratio of the molecular weight of the working fluid to that of the NCG has a very definite effect on the shape of this distribution. Some of the effects are quite similar to the well-established data on stationary heat pipes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal of Heat and Mass Transfer; 21; Feb. 197
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  • 12
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    Surface waves generated by shallow underwater explosions (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Surface water waves generated by surface and near surface point explosions are calculated. Taking the impulse distribution imparted at the water surface by the explosion as the overriding mechanism for transferring energy of the explosive to surface wave motion, the linearized theory of Kranzer and Keller is used to obtain the wave displacement in the far field. The impulse distribution is obtained by integrating the pressure wave over an appropriate time interval on a horizontal surface just beneath the undisturbed water surface. For surface explosions, a modified form of the similarity method first used by Collins and Holt is used to obtain the flow field. In the case of submerged explosions, the flow field is estimated by making necessary modifications to Sedov's similarity solution to account for the venting that accompanies the interaction of the leading (blast) wave with the ocean surface. Surface waves generated by a charge at six depths of placement (0.15 m, 0.30 m, 0.61 m, 0.91 m, 1.37 m, 3.05 m) are considered in addition to surface explosions. The results seem to support the existence of an upper critical depth phenomenon (of the type already established for chemical explosions) for point (nuclear) explosions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 21; Oct. 197
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  • 13
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    Navier-Stokes solutions using Stetter's method (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Compressible Navier-Stokes equations for quasi-one-dimensional flow in a converging-diverging nozzle have been solved using Stetter's three-step predictor-corrector technique. Particular emphasis is given to the minimum iterative step feature for steady-state solutions. It is found that for the nonviscous-dominated case, Stetter's method attains the steady-state solution in the fewest steps when compared to four other currently used techniques.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 16; Sept
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  • 14
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    Predictive capabilities of series solutions for laminar free convection boundary layer heat transfer (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Various types of series solutions for predicting laminar, free-convection boundary-layer heat transfer over both isothermal and nonisothermal boundaries are reviewed. The methods include finite difference, Merk series, Blasius series, and Goertler series. Comparative results are presented for heat transfer over an isothermal, horizontal, elliptical cylinder in both slender and blunt configurations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 15
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    Coefficient matrices for implicit finite difference solution of the inviscid fluid conservation law equations (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Although the Navier-Stokes equations describe most flows of interest in aerodynamics, the inviscid conservation law equations may be used for small regions with viscous forces. Thus, Euler equations and several time-accurate finite difference procedures, explicit and implicit, are discussed. Although implicit techniques require more computational work, they permit larger time steps to be taken without instability. It is noted that the Jacobian matrices for Euler equations in conservation-law form have certain eigenvalue-eigenvector properties which may be used to construct conservative-form coefficient matrices. This reduces the computation time of several implicit and semiimplicit schemes. Extensions of the basic approach to other areas are suggested.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Computer Methods in Applied Mechanics and Engineering; 13; Feb. 197
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  • 16
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    The Wiener-Hermite expansion applied to decaying isotropic turbulence using a renormalized time-dependent base (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The problem of decaying isotropic turbulence has been studied using a Wiener-Hermite expansion with a renormalized time-dependent base. The theory is largely deductive and uses no modeling approximations. It has been found that many properties of large-Reynolds-number turbulence can be calculated (at least for moderate time) using the moving-base expansion alone. Such properties found are the spectrum shape in the dissipation range, the Kolmogorov constant, and the energy cascade in the inertial subrange. Furthermore, by using a renormalization scheme, it is possible to extend the calculation to larger times and to initial conditions significantly different from the equilibrium form. If the initial spectrum is the Kolmogorov spectrum perturbed with a spike or dip in the inertial subrange, the process proceeds to eliminate the perturbation and relax to the preferred spectrum shape. The turbulence decays with the proper dissipation rate, and several other properties are found to agree with measured data. The theory is also used to calculate the energy transfer and the flatness factor of turbulence.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 85; Mar. 21
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  • 17
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    Steady flow of a non-Newtonian fluid through a contraction (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A steady-state analysis is conducted to examine the basic flow structure of a non-Newtonian fluid in a domain including an inflow region, a contraction region, and an outflow region. A Cartesian grid system is used throughout the entire flow domain, including the contraction region, thus creating an irregular grid cell structure adjacent to the curved boundary. At node points adjacent to the curved boundary symmetry conditions are derived for the different flow variables in order to solve the governing difference equations. Attention is given to the motion and non-Newtonian constitutive equations, the boundary conditions, the numerical modeling of the non-Newtonian equations, the stream function contour lines for the non-Newtonian fluid, the vorticity contour lines for the non-Newtonian fluid, the velocity profile across the contraction, and the shear stress contour lines for the non-Newtonian fluid.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Computational Physics; 27; Apr. 197
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  • 18
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    Wall region of a relaxing three-dimensional incompressible turbulent boundary layer (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A three-dimensional turbulent boundary layer relaxing behind a transverse hump (shaped as a 30-deg swept 5-ft chord wing-type model) was studied in a low-speed wind tunnel. Data obtained with hot-wire probes showed that the apparent dimensionless velocity profiles in the viscous sublayer prevail universally; evidence for wall similarity in the relaxing flow field was confirmed in the form of a log law. An unusual region of slightly decreasing cross-flow angle was found in collateral regions, and a near-wall noncollateral flow was posited. Streamwise relaxation of the mean flow field was also investigated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 85; Mar. 7
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  • 19
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    An efficient explicit-implicit-characteristic method for solving the compressible Navier-Stokes equations (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Explicit, implicit, and characteristic finite-difference methods are applied to solve model equations representative of the compressible Navier-Stokes equations. An approach is then formulated for solving the Navier-Stokes equation at high Reynolds numbers. The approach has drastically reduced the computation time required to obtain viscous flow solutions. Computational results for shock wave separated flows are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 20
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    The computation of incompressible, three-dimensional flows in containers with extensible walls (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The theoretical study of flow in biological vascular systems is made very difficult in connection with local and temporal changes of the cross section. Experimental investigations with the aid of model tests are, however, not enough for a solution of the problems, and numerical solutions are more and more employed for a description of such flows. A description is presented of a difference procedure for the solution of the complete Navier-Stokes equations with curvilinear coordinates for three-dimensional flows in containers. The integration of the Navier-Stokes equations for flows in containers with rigid and moving walls is considered.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 21
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    Thermal response behavior of boundary-layer flows (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: This paper presents an approximate, but general, analysis for the thermal response behavior of incompressible, constant property, laminar boundary layer flow over a smooth object of arbitrary shape. It encompasses the classic time-dependent Leveque problem as its special case. Comparisons with available data show that, for fluids with Prandtl number of the order of unity or larger, this analytical solution is able to provide reasonably accurate results for most engineering applications. Under certain restrictive conditions, it can also be used to predict the thermal response of a compressible boundary layer flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal of Heat and Mass Transfer; 21; June 197
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  • 22
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    A finite element thermal analysis procedure for several temperature-dependent parameters (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A finite-element thermal analysis procedure for elements with several temperature-dependent thermal parameters is presented. The procedure, based on an application of the Newton-Raphson iteration technique, is formulated by resolving element matrices into component matrices, one component for each thermal parameter. Component conductance matrices are evaluated by assuming constant thermal parameters within an element and are computed once per unit thermal parameter. Significant savings in computer time result from the unit thermal parameter concept. The solution procedure applied to a convectively cooled structure with significantly varying thermal parameters converged in four iterations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 23
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    The free shear layer tone phenomenon and probe interference (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The reported investigation shows that the hot-wire probe induces stable upstream oscillations in a free shear layer, similar to the jet edge tone mechanism. This effect can be significant also in measurements involving large-scale organized structure, conditional sampling, space-time correlation, and convection velocity, when a reference or indicator probe may be used near the origin of the free shear layer. It appears that even in a free shear layer without any wedge, an object in the flow sufficiently downstream can also provide feedback to the flow upstream. A description is given of the edge-tone phenomenon which is observed when a thin slit jet impinges on a plane wedge. Attention is given to the free shear layer tone induced by a hot-wire probe, the free shear layer tone phenomenon, and shear layer tone eigenvalues and eigenfunctions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 87; July 26
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  • 24
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    A procedure for computation of fully stalled flows in two-dimensional passages (1978)
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    Publication Date: 2011-08-17
    Description: A procedure is described for computation of incompressible, steady, two-dimensional flows in fully stalled diffusers with plenum exit. The procedure is successful in predicting pressure distributions and patterns to the accuracy of the data. The procedure employs a zonal model; this maintains close connections between the modeling and the physics thereby providing insight into critical aspects of modeling separated flows. The procedure presented is also convenient for computing unstalled flows in passages with turbulent boundary layers for either direct or indirect design problems. Computing times are well within engineering feasibility. The concepts developed can be extended to other classes of separated flows; some of these extensions have already been completed and are referenced.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 25
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    A stereoscopic visual study of coherent structures in turbulent shear flow (1978)
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    Publication Date: 2011-08-17
    Description: Stereoscopic photography was used to record the three-dimensional motions of fluid elements along a flat-plate turbulent boundary layer flow. The outer region of the boundary layer was dominated by the formation and convection of transverse vortices, formed at the high-speed front between low- and high-speed fluid elements. Vortical motions observed in the wall region consisted of (1) motions of single particles around part of a circle, (2) streamwise vortices, and (3) transverse vortices.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 89; Nov. 28
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  • 26
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    Interaction of a strong blast wave with a free surface (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: When a point source explosion is initiated at the ocean surface, the shock propagated into the water is reflected at the surface as a centered expansion wave. The solution in the neighborhood of the interaction point is obtained by writing the equations of motion in the appropriate similarity variables and then changing the independent variables to polar coordinates based at the interaction point. From the zero-order solution of the resulting equations the slopes of boundaries at the interaction point are obtained. A first-order perturbation of this solution provides more accurate representation of the flow variables and the curvature of the shock surface near the interaction point.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids; 21; Oct. 197
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  • 27
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    Kinetic model of turbulence in an incompressible fluid (1978)
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    Publication Date: 2011-08-17
    Description: A statistical description of turbulence in an incompressible fluid obeying the Navier-Stokes equations is proposed, where pressure is regarded as a potential for the interaction between fluid elements. A scaling procedure divides a fluctuation into three ranks representing the three transport processes of macroscopic evolution, transport property, and relaxation. Closure is obtained by relaxation, and a kinetic equation is obtained for the fluctuation of the macroscopic rank of the distribution function. The solution gives the transfer function and eddy viscosity. When applied to the inertia subrange of the energy spectrum the analysis recovers the Kolmogorov law and its numerical coefficient.
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  • 28
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    Prediction of unsteady separated flows on oscillating airfoils (1978)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Techniques for calculating high Reynolds number flow around an airfoil undergoing dynamic stall are reviewed. Emphasis is placed on predicting the values of lift, drag, and pitching moments. Methods discussed include: the discrete potential vortex method; thin boundary layer method; strong interaction between inviscid and viscous flows; and solutions to the Navier-Stokes equations. Empirical methods for estimating unsteady airloads on oscillating airfoils are also described. These methods correlate force and moment data from wind tunnel tests to indicate the effects of various parameters, such as airfoil shape, Mach number, amplitude and frequency of sinosoidal oscillations, mean angle, and type of motion.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Three Dimensional and Unsteady Separation at High Reynolds No.; 8 p
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  • 29
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    Introduction to unsteady aspects of separation in subsonic and transonic flow (1978)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Unsteady flow phenomena are reviewed with emphasis on separated flow in the subsonic and transonic regimes. Specific topics discussed include external flows past bluff bodies, unsteady separation on slender bodies, and internal flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Three Dimensional and Unsteady Separation at High Reynolds No.; 8 p
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  • 30
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    Phenomenological aspects of quasi-stationary controlled and uncontrolled three-dimensional flow separations (1978)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Quasi-steady three dimensional separated flows about bodies of large fineness ratio operating at large angles of incidence or yaw are discussed. The general character of the three dimensional attached boundary layer, the concept of limiting streamlines, and the physics of three dimensional separation and reattachment are among the factors considered. Specific examples are given. The advantages of swept, sharp edges that generate controlled (or fixed) three dimensional flow separations on a vehicle, due to the qualitatively unchanging flow field developed throughout the range of flight conditions, are emphasized.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Three Dimensional and Unsteady Separation at High Reynolds No.; 52 p
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  • 31
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    Status and future prospects of using numerical methods to study complex flows at High Reynolds numbers (1978)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The calculation of flow fields past aircraft configuration at flight Reynolds numbers is considered. Progress in devising accurate and efficient numerical methods, in understanding and modeling the physics of turbulence, and in developing reliable and powerful computer hardware is discussed. Emphasis is placed on efficient solutions to the Navier-Stokes equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Three Dimensional and Unsteady Separation at High Reynolds No.; 2 p
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    Some unsteady separation problems for slender bodies (1978)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The unsteady Kutta-Joukowski condition, dynamic stall on oscillating airfoils, and unsteady shock wave-boundary layer interaction are discussed. Emphasis is placed on developing reliable prediction techniques and suppression of unsteady separation on oscillating control surfaces, wings, and rotating blades to improve aerodynamic stability.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Three Dimensional and Unsteady Separation at High Reynolds No.; 11 p
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  • 33
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    An improved viscous characteristics analysis program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An improved two dimensional characteristics analysis program is presented. The program is built upon the foundation of a FORTRAN program entitled Analysis of Supersonic Combustion Flow Fields With Embedded Subsonic Regions. The major improvements are described and a listing of the new program is provided. The subroutines and their functions are given as well as the input required for the program. Several applications of the program to real problems are qualitatively described. Three runs obtained in the investigation of a real problem are presented to provide insight for the input and output of the program.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1289 , L-12320
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  • 34
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    SSV Generic OFT first stage ascent base convective heating environments (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Space Shuttle Vehicle (SSV) base convective heating environments during the recirculated flow time segment of first stage ascent were determined for the Generic OFT trajectory and performance conditions. These environments are presented in the attachments as cold wall convective heat transfer coefficients for individual or groups of design points for all affected SSV base surfaces. Two gas recovery temperatures applicable to upper and lower base region surfaces are also included. The environments were based upon magnitudes and trends from analysis of data taken during Base Heating Tests IH-39, IH-75, and IH-83. The plume heating trajectory and performance data were supplied by Rockwell International for both the OFT-1 Generic Mission A and Mission C.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-161499 , RTR-014-6
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    Addendum to SSV Generic OFT First Stage Ascent Base Convective Heating Environments (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Convective environments for OFT Mission C are presented in graphs for first stage convective heating to the internal surfaces of the OMS nozzle, to the aft facing 8 and 9 RCS nozzles, and to the base (trailing edge) of the vertical tail.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-161497 , RTR-014-8
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    Stochastic partial differential equations in turbulence related problems (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The theory of stochastic partial differential equations (PDEs) and problems relating to turbulence are discussed by employing the theories of Brownian motion and diffusion in infinite dimensions, functional differential equations, and functional integration. Relevant results in probablistic analysis, especially Gaussian measures in function spaces and the theory of stochastic PDEs of Ito type, are taken into account. Linear stochastic PDEs are analyzed through linearized Navier-Stokes equations with a random forcing. Stochastic equations for waves in random media as well as model equations in turbulent transport theory are considered. Markovian models in fully developed turbulence are discussed from a stochastic equation viewpoint.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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    On the development of packets of surface gravity waves moving over an uneven bottom (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The object of study is the evolution of packets of gravity waves moving over variable depth, in particular, the transformation of packets moving into a shelf of increased or decreased depth. The variable-coefficient nonlinear Schroedinger equation with inhomogeneous term is derived for gravity waves moving over an uneven bottom. A solution for an envelope-hole soliton moving over variable depth is obtained when the amplitude-length ratio of the soliton is small. For the shelf problem, it is shown that the first soliton on the shelf will be the one with smallest depression, and the last will have greatest depression. This is in contrast to Korteweg-de Vries soliton fission.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Zeitschrift fuer angewandte Mathematik und Physik; 29; Nov. 25
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  • 38
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    Vapor transport mechanisms (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Raman scattering furnace for investigating vapor transport mechanisms was completed and checked out. Preliminary experiments demonstate that a temperature resolution of plus and minus 5 C is possible with this system operating in a backscatter mode. In the experiments presented with the GeI 4 plus excess Ge system at temperatures up to 600 C, only the GeI4 band at 150 cm superscript minus 1 was observed. Further experiments are in progress to determine if GeI2 does become the major vapor species above 440 C.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-150824
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  • 39
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    An old integration scheme for compressible flows revisited, refurbished and put to work (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A scheme for integrating the Euler equations of compressible flow in any hyperbolic case is presented. The scheme relies on the concept of characteristics but is strictly a finite difference scheme. Improvements in accuracy and physical consistence due to the scheme are discussed and results of its application to complex flows are shown.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-157755 , POLY-M/AE-78-22
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  • 40
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    Studies of convection in a solidifying system with surface tension at reduced gravity (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The low gravity environment of Earth's orbit is being seriously considered for experimentation on the production of materials in space. Most of such materials processes inevitably involve either the solidification of melt or the melting of solids. Inherent in most fluid mechanisms with temperature gradients is convective motion. A study is presented for the onset of convection in a solidifying system in an environment which is similar to that encountered in space processing. Since the study is for a low gravity condition, the only driving mechanism considered is that due to the variation of surface tension force at the free surface of the melt layer. Two simple solidification models were considered, one in which the solidification process enters in the perturbation system and another in which the melt is solidifying at a constant rate. The results show that the solidification process will bring about convection in the melt earlier than otherwise.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3051 , M-265
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  • 41
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    Evaluation of AAFE apparatus to measure residual and transient convection in zero-gravity (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An evaluation apparatus which photographs convective and diffusive flows in crystal growth experiments is presented. Results in the following catagories are reported: (1) Human factors; (2) Electrical and mechanical; (3) Optical performance; and (4) Thermal performance.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78191
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  • 42
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    Equations of motion and two-equation turbulence model for plane or axisymmetric turbulent flows in body-oriented orthogonal curvilinear coordinates and mass-averaged dependent variables (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The full Navier-Stokes time-dependent, compressible, turbulent, mean-flow equations in mass-averaged variables for plane or axisymmetric flow are presented. The equations are derived in a body-oriented, orthogonal, curvilinear coordinate system. Turbulence is modelled by a system of two equations for mass-averaged turbulent kinetic energy and dissipation rate proposed. These equations are rederived and some new features are discussed. A system of second order boundary layer equations is then derived which includes the effects of longitudinal curvature and the normal pressure gradient. The Wilcox and Chambers approach is used in considering effects of streamline curvature on turbulence phenomena in turbulent boundary layer type flows. Their two-equation turbulence model with curvature terms are rederived for the cases considered in the present report. The derived system equations serves as a basis for an investigation of problems where streamline curvature is of the order of the characteristic length in the longitudinal direction.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3025 , UTIAS-225
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  • 43
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    Heat transfer distributions induced by elevon deflections on swept wings and adjacent surfaces at Mach 6 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Surface heat transfer distributions are presented for swept wing semispan models having trailing edge elevon ramp angles of 0, 10, 20, and 30 degrees. The wing sweepback angles are 0, 50, and 70 degrees. The models have attachable cylindrical and flat plate center bodies and various attachable wing-tip fins. The data, obtained for a 0 degree angle of attack, a free stream Mach number of 6, and a wing root chord Reynolds number of about 17,000,000, reveal considerably larger regions of elevon induced thermal loads on adjacent surfaces than would be suggested by fully attached flow analyses.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-74045 , L-11461
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  • 44
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    Reinforced carbon-carbon oxidation behavior in convective and radiative environments (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Reinforced carbon-carbon, which is used as thermal protection on the space shuttle orbiter wing leading edges and nose cap, was tested in both radiant and plasma arcjet heating test facilities. The test series was conducted at varying temperatures and pressures. Samples tested in the plasma arcjet facility had consistently higher mass loss than those samples tested in the radiant facility. A method using the mass loss data is suggested for predicting mission mass loss for specific locations on the Orbiter.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1284 , S-485
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  • 45
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    Analysis of turbulent free jet hydrogen-air diffusion flames with finite chemical reaction rates (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The nonequilibrium flow field resulting from the turbulent mixing and combustion of a supersonic axisymmetric hydrogen jet in a supersonic parallel coflowing air stream is analyzed. Effective turbulent transport properties are determined using the (K-epsilon) model. The finite-rate chemistry model considers eight reactions between six chemical species, H, O, H2O, OH, O2, and H2. The governing set of nonlinear partial differential equations is solved by an implicit finite-difference procedure. Radial distributions are obtained at two downstream locations of variables such as turbulent kinetic energy, turbulent dissipation rate, turbulent scale length, and viscosity. The results show that these variables attain peak values at the axis of symmetry. Computed distributions of velocity, temperature, and mass fraction are also given. A direct analytical approach to account for the effect of species concentration fluctuations on the mean production rate of species (the phenomenon of unmixedness) is also presented. However, the use of the method does not seem justified in view of the excessive computer time required to solve the resulting system of equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3024 , UTIAS-224
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  • 46
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    Liquid propellant reorientation in a low-gravity environment (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An existing empirical analysis relating to the reorientation of liquids in cylindrical tanks due to propulsive settling in a low gravity environment was extended to include the effects of geyser formation in the Weber number range from 4 to 10. Estimates of the minimum velocity increment required to be imposed on the propellant tank to achieve liquid reorientation were made. The resulting Bond numbers, based on tank radius, were found to be in the range from 3 to 5, depending upon the initial liquid fill level, with higher Bond number required for high initial fill levels. The resulting Weber numbers, based on tank radius and the velocity of the liquid leading edge, were calculated to be in the range from 6.5 to 8.5 for cylindrical tanks having a fineness ratio of 2.0, with Weber numbers of somewhat greater values for longer cylindrical tanks. It, therefore, appeared to be advantageous to allow small geysers to form and then dissipate into the surface of the collected liquid in order to achieve the minimum velocity increment. The Bond numbers which defined the separation between regions in which geyser formation did and did not occur due to propulsive settling in a spherical tank configuration ranged from 2 to 9 depending upon the liquid fill level.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78969 , E-9716
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  • 47
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    Aerodynamic heating in gaps of thermal protection system tile arrays in laminar and turbulent boundary layers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental heat-transfer investigation was conducted on two staggered arrays of metallic tiles in laminar and turbulent boundary layers. This investigation was conducted for two purposes. The impingement heating distribution where flow in a longitudinal gap intersects a transverse gap and impinges on a downstream blocking tile was defined. The influence of tile and gap geometries was analyzed to develop empirical relationships for impingement heating in laminar and turbulent boundary layers. Tests were conducted in a high temperature structures tunnel at a nominal Mach number of 7, a nominal total temperature of 1800 K, and free-stream unit Reynolds numbers from 1.0 x 10 million to 4.8 x 10 million per meter. The test results were used to assess the impingement heating effects produced by parameters that include gap width, longitudinal gap length, slope of the tile forward-facing wall, boundary-layer displacement thickness, Reynolds number, and local surface pressure.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1187 , L-12009
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  • 48
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    Analysis of strong-interaction dynamic stall for laminar flow on airfoils (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A compressible Navier-Stokes solution procedure is applied to the flow about an isolated airfoil. Two major problem areas were investigated. The first area is that of developing a coordinate system and an initial step in this direction has been taken. An airfoil coordinate system obtained from specification of discrete data points developed and the heat conduction equation has been solved in this system. Efforts required to allow the Navier-Stokes equations to be solved in this system are discussed. The second problem area is that of obtaining flow field solutions. Solutions for the flow about a circular cylinder and an isolated airfoil are presented. In the former case, the prediction is shown to be in good agreement with data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2969 , R77-912030-17
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    Recent turbulent drag reduction research at Langley Research Center (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three areas are discussed: oscillatory longitudinal curvature, large eddy breakup devices, and small longitudinal surface striations. The first two concepts produced sizable local turbulent skin friction reductions, but further research is required to optimize the effect, reduce parasitic device drag, and provide a net increase in vehicle performance. The surface striations, due to large wetted area increased for a given planform, have not yet yielded a planform-averaged skin friction reduction. Heat transfer data indicated such surfaces may have useful application in heat exchangers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78688
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    Influence of free-stream disturbances on boundary-layer transition (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Considerable experimental evidence exists which shows that free stream disturbances (the ratio of root-mean-square pressure fluctuations to mean values) in conventional wind tunnels increase with increasing Mach number at low supersonic to moderate hypersonic speeds. In addition to local conditions, the free stream disturbance level influences transition behavior on simple test models. Based on this observation, existing noise transition data obtained in the same test facility were correlated for a large number of reference sharp cones and flat plates and are shown to collapse along a single curve. This result is a significant improvement over previous attempts to correlate noise transition data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78635 , L-11905
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    Fabrication and test of a variable conductance heat pipe (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A variable conductance heat pipe (VCHP) with feedback control was fabricated with a reservoir-condenser volume ratio of 10 and an axially grooved action section. Tests of the heat transport capability were greater than or equal to the analytical predictions for the no gas case. When gas was added, the pipe performance degraded by 18% at zero tilt as was expected. The placement of the reservoir heater and the test fixture cooling fins are believed to have caused a superheated vapor condition in the reservoir. Erroneously high reservoir temperature indications resulted from this condition. The observed temperature gradients in the reservoir lend support to this theory. The net result was higher than predicted reservoir temperatures. Also, significant increases in minimum heat load resulted for controller set point temperatures higher than 0 C. At 30 C, control within the tolerance band was maintained, but high reservoir heater power was required. Analyses showed that control is not possible for reasonably low reservoir heater power. This is supported by the observation of a significant reservoir heat leak through the condenser.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-156712 , SD-78-AP-0011
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  • 52
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    Boundary layer analysis of a Centaur standard shroud (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical boundary layer investigation was carried out in conjunction with an experimental wind tunnel test to determine the discharge characteristics of the Centaur shroud ascent vent system on the Titan/Centaur launch vehicle. This involved estimating the effect of the local boundary layers on the vent discharge for vehicle Mach numbers ranging from 0.8 to 1.56. The growth of the boundary layer along the vehicle was influenced by the interaction with flanges protruding into the flow and by the longitudinal corrugations in the vehicle surface. The effects of the flange and corrugations were treated by approximate techniques. In addition, boundary layer calculations were made for a 3 percent model of the launch vehicle compared with experimental results.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78843 , E-9557
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    A well posed boundary value problem in transonic gas dynamics (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A boundary value problem for the Tricomi equation was studied in connection with transonic gas dynamics. The transformed equation delta u plus 1/3Y u sub Y equals 0 in canonical coordinates was considered in the complex domain of two independent complex variables. A boundary value problem was then set by prescribing the real part of the solution on the boundary of the real unit circle. The Dirichlet problem in the upper unit semicircle with vanishing values of the solution at Y = 0 was solved explicitly in terms of the hypergeometric function for the more general Euler-Poisson-Darboux equation. An explicit representation of the solution was also given for a mixed Dirichlet and Neumann problem for the same equation and domain.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-155925 , COO-3077-149
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  • 54
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    Method for calculating convective heat-transfer coefficients over turbine vane surfaces (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for calculating laminar, transitional, and turbulent convective heat-transfer coefficients for turbine vane surfaces is described. An approximate integral solution method produced results in good agreement with a finite-difference solution. Comparisons between the two are presented. The integral solution results agreed well with the finite-difference solution results in the laminar and turbulent regions. Differences in calculating the start of transition produced a later starting point for the approximate integral solution's transitional flow regime.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1134 , E-9324
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  • 55
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    Evaluation of a large capacity heat pump concept for active cooling of hypersonic aircraft structure (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of engineering analyses assessing the conceptual feasibility of a large capacity heat pump for enhancing active cooling of hypersonic aircraft structure are presented. A unique heat pump arrangement which permits cooling the structure of a Mach 6 transport to aluminum temperatures without the aid of thermal shielding is described. The selected concept is compatible with the use of conventional refrigerants, with Freon R-11 selected as the preferred refrigerant. Condenser temperatures were limited to levels compatible with the use of conventional refrigerants by incorporating a unique multipass condenser design, which extracts mechanical energy from the hydrogen fuel, prior to each subsequent pass through the condenser. Results show that it is technically feasible to use a large capacity heat pump in lieu of external shielding. Additional analyses are required to optimally apply this concept.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145301
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  • 56
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    Magnetic heat pumping (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A ferromagnetic or ferrimagnetic element is used to control the temperature and applied magnetic field of the element to cause the state of the element as represented on a temperature-magnetic entropy diagram to repeatedly traverse a loop. The loop may have a first portion of concurrent substantially isothermal or constant temperature and increasing applied magnetic field, a second portion of lowering temperature and constant applied magnetic field, a third portion of isothermal and decreasing applied magnetic field, and a fourth portion of increasing temperature and constant applied magnetic field. Other loops may be four-sided, with two isotherms and two adiabats. Preferably, a regenerator is used to enhance desired cooling or heating effects, with varied magnetic fields, or varying temperatures including three-sided figures traversed by the representative point.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 57
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    Effects of mass addition on blunt-body boundary-layer transition and heat transfer (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The model bodies tested at Mach number 7.32 were hemispheres, blunt cones, and spherical segments. The mass addition consisted of air ejected through porous forward surfaces of the models. The experimental data consisted of heat transfer measurements from which boundary layer transitions were deduced. The data verified various applicable boundary layer codes in the laminar and transitional flow regimes. Empirical heating rate data correlations were developed for the laminar and turbulent flow regimes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1139 , A-7169
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  • 58
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    TACT1, a computer program for the transient thermal analysis of a cooled turbine blade or vane equipped with a coolant insert. 1. Users manual (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program to calculate transient and steady state temperatures, pressures, and coolant flows in a cooled, axial flow turbine blade or vane with an impingement insert is described. Coolant side heat transfer coefficients are calculated internally in the program, with the user specifying either impingement or convection heat transfer at each internal flow station. Spent impingement air flows in a chordwise direction and is discharged through the trailing edge and through film cooling holes. The ability of the program to handle film cooling is limited by the internal flow model. Sample problems, with tables of input and output, are included in the report. Input to the program includes a description of the blade geometry, coolant supply conditions, outside thermal boundary conditions, and wheel speed. The blade wall can have two layers of different materials, such as a ceramic thermal barrier coating over a metallic substrate. Program output includes the temperature at each node, the coolant pressures and flow rates, and the inside heat-transfer coefficients.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1271 , E-9554
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  • 59
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    A mean spherical model for soft potentials: The hard core revealed as a perturbation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mean spherical approximation for fluids is extended to treat the case of dense systems interacting via soft-potentials. The extension takes the form of a generalized statement concerning the behavior of the direct correlation function c(r) and radial distribution g(r). From a detailed analysis that views the hard core portion of a potential as a perturbation on the whole, a specific model is proposed which possesses analytic solutions for both Coulomb and Yukawa potentials, in addition to certain other remarkable properties. A variational principle for the model leads to a relatively simple method for obtaining numerical solutions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-157771 , TR-4009
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  • 60
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    Extended Development of Variable Conductance Heat Pipes (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A high-capacity vapor-modulated heat pipe was designed and tested. In 1977, a program was undertaken to use the aforementioned heat pipe to study protection from freezing-point failure, increase control sensitivity, and transient behavior under a wide range of operating conditions in order to determine the full performance potential of the heat pipe. A new concept, based on the vapor-induced-dry-out principle, was developed for passive feedback temperature control as a heat pipe diode. This report documents this work and describes: (1) the experimental and theoretical investigation of the performance of the vapor-modulated heat pipe; and (2) the design, fabrication and test of the heat pipe diode.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-152183 , TRW-31183-6001-RU-00
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    On the period of the coherent structure in boundary layers at large Reynolds numbers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The period of the large coherent structure in a subsonic, compressible, turbulent boundary layer was determined using the autocorrelation of the velocity and pressure fluctuations for Reynolds numbers between 5,000 and 35,000. In low Reynolds number flows the overall correlation period scaled with the outer variables - namely, the free stream velocity and the boundary layer thickness.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78477 , A-7380
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  • 62
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    Correlation of laser velocimeter measurements over a wing with results of two prediction techniques (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field at the center line of an unswept wing with an aspect ratio of eight was determined using a two dimensional viscous flow prediction technique for the flow field calculation, and a three dimensional potential flow panel method to evaluate the degree of two dimensionality achieved at the wing center line. The analysis was made to provide an acceptable reference for comparison with velocity measurements obtained from a fringe type laser velocimeter optics systems operating in the backscatter mode in the Langley V/STOL tunnel. Good agreement between laser velocimeter measurements and theoretical results indicate that both methods provide a true representation of the velocity field about the wing at angles of attack of 0.6 and 4.75 deg.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1168 , L-11980
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    Cryogenic-coolant He-4-superconductor interaction (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The thermodynamic and thermal interaction between a type 2 composite alloy and cryo-coolant He4 was studied with emphasis on post quench phenomena of formvar coated conductors. The latter were investigated using a heater simulation technique. Overall heat transfer coefficients were evaluated for the quench onset point. Heat flux densities were determined for phenomena of thermal switching between a peak and a recovery value. The study covered near saturated liquid, pressurized He4, both above and below the lambda transition, and above and below the thermodynamic critical pressure. In addition, friction coefficients for relative motion between formvar insulated conductors were determined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2963 , UCLA-ENG-7767
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  • 64
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    A computer program for calculating laminar and turbulent boundary layers for two-dimensional time-dependent flows (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program is described which provides solutions of two dimensional equations appropriate to laminar and turbulent boundary layers for boundary conditions with an external flow which fluctuates in magnitude. The program is based on the numerical solution of the governing boundary layer equations by an efficient two point finite difference method. An eddy viscosity formulation was used to model the Reynolds shear stress term. The main features of the method are briefly described and instructions for the computer program with a listing are provided. Sample calculations to demonstrate its usage and capabilities for laminar and turbulent unsteady boundary layers with an external flow which fluctuated in magnitude are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78470 , A-7340
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  • 65
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    Inviscid, nonadiabatic flow fields over blunt, sonic corner bodies for outer planet entry conditions by a method of integral relations (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been made into the ability of a method of integral relations to calculate inviscid zero degree angle of attack, radiative heating distributions over blunt, sonic corner bodies for some representative outer planet entry conditions is investigated. Comparisons have been made with a more detailed numerical method, a time asymptotic technique, using the same equilibrium chemistry and radiation transport subroutines. An effort to produce a second order approximation (two-strip) method of integral relations code to aid in this investigation is also described and a modified two-strip routine is presented. Results indicate that the one-strip method of integral relations cannot be used to obtain accurate estimates of the radiative heating distribution because of its inability to resolve thermal gradients near the wall. The two-strip method can sometimes be used to improve these estimates; however, the two-strip method has only a small range of conditions over which it will yield significant improvement over the one-strip method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1133 , L-11944
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  • 66
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    Direct measurements and analysis of skin friction and cooling downstream of multiple flush-slot injection into a turbulent Mach 6 boundary layer (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were conducted to determine the reduction in surface skin friction and the effectiveness of surface cooling downstream of one to four successive flush slots injecting cold air at an angle of 10 deg into a turbulent Mach 6 boundary layer. Data were obtained by direct measurement of surface shear and equilibrium temperatures, respectively. Increasing the number of slots decreased the skin friction, but the incremental improvement in skin-friction reduction decreased as the number of slots was increased. Cooling effectiveness was found to improve, for a given total mass injection, as the number of slots was increased from one to four. Comparison with previously reported step-slot data, however, indicated that step slots with tangential injection are more effective for both reducing skin friction and cooling than the present flush-slot configuration. Finite-difference predictions are in reasonable agreement with skin-friction data and with boundary-layer profile data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1176 , L-11950
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  • 67
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    A high order accurate finite element algorithm for high Reynolds number flow prediction (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A Galerkin-weighted residuals formulation is employed to establish an implicit finite element solution algorithm for generally nonlinear initial-boundary value problems. Solution accuracy, and convergence rate with discretization refinement, are quantized in several error norms, by a systematic study of numerical solutions to several nonlinear parabolic and a hyperbolic partial differential equation characteristic of the equations governing fluid flows. Solutions are generated using selective linear, quadratic and cubic basis functions. Richardson extrapolation is employed to generate a higher-order accurate solution to facilitate isolation of truncation error in all norms. Extension of the mathematical theory underlying accuracy and convergence concepts for linear elliptic equations is predicted for equations characteristic of laminar and turbulent fluid flows at nonmodest Reynolds number. The nondiagonal initial-value matrix structure introduced by the finite element theory is determined intrinsic to improved solution accuracy and convergence. A factored Jacobian iteration algorithm is derived and evaluated to yield a consequential reduction in both computer storage and execution CPU requirements while retaining solution accuracy.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-157309
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  • 68
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    An experimental documentation of pressure gradient and Reynolds number effects on compressible turbulent boundary layers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Attached supersonic turbulent boundary layers, with a wide range of adverse pressure gradient strengths, are investigated for Reynolds numbers from 11.7 x 1 million to 314 x 1 million. Surface pressure and surface shear measurements were obtained for six flow fields over the entire Reynolds number range. In addition, two flow fields - one with a moderate pressure gradient and the other with a severe pressure gradient - are thoroughly documented at a single Reynolds number. This experimental documentation includes both mean and fluctuating profiles throughout the flow field, and is sufficient to define the complete flow field, including the upstream undisturbed flow region.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78488 , A-7426
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  • 69
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    Induced velocity field of a jet in a crossflow (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation of a subsonic round jet exhausting perpendicularly from a flat plate into a subsonic crosswind of the same temperature was conducted. Velocity and pressure measurements were made in planes perpendicular to the path of the jet for ratios of jet velocity to crossflow velocity ranging from 3 to 10. The results of these measurements are presented in tabular and graphical forms. A pair of diffuse contrarotating vortices is identified as a significant feature of the flow, and the characteristics of the vortices are discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1087 , L-11624
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  • 70
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    Solution of transonic flows by an integro-differential equation method (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Solutions of steady transonic flow past a two-dimensional airfoil are obtained from a singular integro-differential equation which involves a tangential derivative of the perturbation velocity potential. Subcritical flows are solved by taking central differences everywhere. For supercritical flows with shocks, central differences are taken in subsonic flow regions and backward differences in supersonic flow regions. The method is applied to a nonlifting parabolic-arc airfoil and to a lifting NACA 0012 airfoil. Results compare favorably with those of finite-difference schemes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78490 , A-7434
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  • 71
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    Laser velocimeter application to oscillatory liquid flows (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A laser velocimeter technique was used to measure the mean velocity and the frequency characteristics of an oscillatory flow component generated with a rotating flapper in liquid flow system at Reynolds numbers approximating 93,000. The velocity information was processed in the frequency domain using a tracker whose output was used to determine the flow spectrum. This was accomplished with the use of an autocorrelator/Fourier transform analyzer and a spectrum averaging analyzer where induced flow oscillations up to 40 Hz were detected. Tests were conducted at a mean flow velocity of approximately 2 m/s. The experimental results show that the laser velocimeter can provide quantitative information such as liquid flow velocity and frequency spectrum with a possible application to cryogenic fluid flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78702
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  • 72
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    Application of second-order turbulent modeling to the prediction of radiated aerodynamic sound (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Ribner formulation of the generation of aerodynamic sound is coupled with predictions of second-order velocity correlations and integral scale to estimate the sound radiated from several complicated jet flows. In particular, it is shown that the sound radiated from a cold swirling jet is greater than from its nonswirling equal thrust counterpart. The noise radiated from the flow field of a multitube suppressor was estimated and compared with an equal thrust diameter Gaussian jet. It is shown that the multitube concept is indeed quieter.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2994
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  • 73
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    Computational flow development for unsteady viscous flows: Foundation of the numerical method (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A procedure is presented for effective consideration of viscous effects in computational development of high Reynolds number flows. The procedure is based on the interpretation of the Navier-Stokes equations as vorticity transport equations. The physics of the flow was represented in a form suitable for numerical analysis. Lighthill's concept for flow development for computational purposes was adapted. The vorticity transport equations were cast in a form convenient for computation. A statement for these equations was written using the method of weighted residuals and applying the Galerkin criterion. An integral representation of the induced velocity was applied on the basis of the Biot-Savart law. Distribution of new vorticity, produced at wing surfaces over small computational time intervals, was assumed to be confined to a thin region around the wing surfaces.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2995
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  • 74
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    Shock capturing finite-difference and characteristic reference plane techniques for the prediction of three-dimensional nozzle-exhaust flowfields (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report summarizes work accomplished under Contract No. NAS1-12726 towards the development of computational procedures and associated numerical. The flow fields considered were those associated with airbreathing hypersonic aircraft which require a high degree of engine/airframe integration in order to achieve optimized performance. The exhaust flow, due to physical area limitations, was generally underexpanded at the nozzle exit; the vehicle afterbody undersurface was used to provide additional expansion to obtain maximum propulsive efficiency. This resulted in a three dimensional nozzle flow, initialized at the combustor exit, whose boundaries are internally defined by the undersurface, cowling and walls separating individual modules, and externally, by the undersurface and slipstream separating the exhaust flow and external stream.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145366
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  • 75
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    Flow compensating pressure regulator (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus for regulating pressure of treatment fluid during ophthalmic procedures is described. Flow sensing and pressure regulating diaphragms are used to modulate a flow control valve. The pressure regulating diaphragm is connected to the flow control valve to urge the valve to an open position due to pressure being applied to the diaphragm by bias means such as a spring. The flow sensing diaphragm is mechanically connected to the flow control valve and urges it to an opened position because of the differential pressure on the diaphragm generated by a flow of incoming treatment fluid through an orifice in the diaphragm. A bypass connection with a variable restriction is connected in parallel relationship to the orifice to provide for adjusting the sensitivity of the flow sensing diaphragm. A multiple lever linkage system is utilized between the center of the second diaphragm and the flow control valve to multiply the force applied to the valve by the other diaphragm and reverse the direction of the force.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 76
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    Flexible pile thermal barrier insulator (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flexible pile thermal barrier insulator included a plurality of upstanding pile yarns. A generally planar backing section supported the upstanding pile yarns. The backing section included a plurality of filler yarns forming a mesh in a first direction. A plurality of warp yarns were looped around said filler yarns and pile yarns in the backing section and formed a mesh in a second direction. A binder prevented separation of the yarns in the backing section.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 77
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    A numerical solution of the Navier-Stokes equations for chemically nonequilibrium, merged stagnation shock layers on spheres and two-dimensional cylinders in air (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of solving the Navier-Stokes equations for chemically nonequilibrium, merged stagnation shock layers on spheres and two-dimensional cylinders are presented. The effects of wall catalysis and slip are also examined. The thin shock layer assumption is not made, and the thick viscous shock is allowed to develop within the computational domain. The results show good comparison with existing data. Due to the more pronounced merging of shock layer and boundary layer for the sphere, the heating rates for spheres become higher than those for cylinders as the altitude is increased.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1227 , M-254
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  • 78
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    Configuration heating for a hypersonic research airplane concept having a 70 deg swept double-delta wing (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The heating on a candidate hypersonic research airplane configuration has been examined experimentally at Mach 6 by the phase-change-paint technique. The configuration has a double-delta wing with tip fins. Phase-change-paint diagrams give heating data for the model top, side, and bottom, with and without deflected elevons for an angle-of-attack range of 0 deg to 24 deg. Nominal Reynolds numbers are on the order of 15,000,000 with supplementary data at length Reynolds number of 4,000,000, which moves the model from the predominantly turbulent into the predominantly laminar regime. Also, intermediate Reynolds numbers were investigated on the lee side for one angle of attack.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1143 , L-11841
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  • 79
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    Simulation of turbulent wall pressure (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A Monte Carlo procedure was developed to simulate turbulent boundary layer wall pressure fluctuations. The approach utilizes much of the newly available conditional sampling information to construct the required distribution functions. Various disturbance wave forms were examined, as well as the effect of frequency-dependent decay. Good agreement between the simulation and experimental data was achieved for root mean square pressure level, power spectrum, and space time correlation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2958
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  • 80
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    Comparison of two computer programs by predicting turbulent mixing of helium in a ducted supersonic airstream (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two parabolic flow computer programs, SHIP (a finite-difference program) and COMOC (a finite-element program), are used for predicting three-dimensional turbulent reacting flow fields in supersonic combustors. The theoretical foundation of the two computer programs are described, and then the programs are applied to a three-dimensional turbulent mixing experiment. The cold (nonreacting) flow experiment was performed to study the mixing of helium jets with a supersonic airstream in a rectangular duct. Surveys of the flow field at an upstream were used as the initial data by programs; surveys at a downstream station provided comparison to assess program accuracy. Both computer programs predicted the experimental results and data trends reasonably well. However, the comparison between the computations from the two programs indicated that SHIP was more accurate in computation and more efficient in both computer storage and computing time than COMOC.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1166 , L-11949
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  • 81
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    Solution of axisymmetric and two-dimensional inviscid flow over blunt bodies by the method of lines (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Comparisons with experimental data and the results of other computational methods demonstrated that very accurate solutions can be obtained by using relatively few lines with the method of lines approach. This method is semidiscrete and has relatively low core storage requirements as compared with fully discrete methods since very little data were stored across the shock layer. This feature is very attractive for three dimensional problems because it enables computer storage requirements to be reduced by approximately an order of magnitude. In the present study it was found that nine lines was a practical upper limit for two dimensional and axisymmetric problems. This condition limits application of the method to smooth body geometries where relatively few lines would be adequate to describe changes in the flow variables around the body. Extension of the method to three dimensions was conceptually straightforward; however, three dimensional applications would also be limited to smooth body geometries although not necessarily to total of nine lines.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1154 , L-11983
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  • 82
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    Wake-shock interaction at a Mach number of 6 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measurements of mean pitot pressure, static pressure, and total temperature were made in the two dimensional turbulent mixing region of a wake downstream of an interaction with a shock-expansion wave system. The results indicated that: (1) the shock increased the mixing, and (2) the expansion field that followed the shock decreased the turbulent mixing. The overall effect of the shock-expansion wave interaction was dependent on the orientation of the expansion wave with respect to the intersecting shock wave. These data could be used to validate nonequilibrium turbulence modeling and numerical solution of the time averaged Navier-Stokes equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1103 , L-11904
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  • 83
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    Aerothermodynamic Assessment of Corrugated Panel Thermal Protection Systems (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of using corrugated panels as a thermal protection system for an advanced space transportation vehicle was investigated. The study consisted of two major tasks: development of improved correlations for wind tunnel heat transfer and pressure data to yield design techniques, and application of the design techniques to determine if corrugated panels have application future aerospace vehicles. A single-stage-to-orbit vehicle was used to assess advantages and aerothermodynamic penalties associated with use of such panels. In the correlation task, experimental turbulent heat transfer and pressure data obtained on corrugation roughened surfaces during wind tunnel testing were analyzed and compared with flat plate data. The correlations and data comparisons included the effects of a large range of geometric, inviscid flow, internal boundary layer, and bulk boundary layer parameters in supersonic and hypersonic flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145317
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  • 84
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    Drag reduction obtained by modifying a standard truck (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A standard two-axle truck with a box-shaped cargo compartment was tested to determine whether significant reductions in aerodynamic drag could be obtained by modifying the front of the cargo compartment. The coastdown method was used to determine the total drag of the baseline vehicle, which had a square-cornered cargo box, and of several modified configurations. Test velocities ranged from 56.3 to 94.6 kilometers per hour (35 to 60 miles per hour). At 88.5 kilometers per hour (55 miles per hour), the aerodynamic drag reductions obtained with the modified configurations ranged from 8 to 30 percent.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-72846 , H-977
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  • 85
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    Forebody and afterbody solutions of the Navier-Stokes equations for supersonic flow over blunt bodies in a generalized orthogonal coordinate system (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A coordinate transformation, which can approximate many different two-dimensional and axisymmetric body shapes with an analytic function, is used as a basis for solving the Navier-Stokes equations for the purpose of predicting 0 deg angle of attack supersonic flow fields. The transformation defines a curvilinear, orthogonal coordinate system in which coordinate lines are perpendicular to the body and the body is defined by one coordinate line. This system is mapped in to a rectangular computational domain in which the governing flow field equations are solved numerically. Advantages of this technique are that the specification of boundary conditions are simplified and, most importantly, the entire flow field can be obtained, including flow in the wake. Good agreement has been obtained with experimental data for pressure distributions, density distributions, and heat transfer over spheres and cylinders in supersonic flow. Approximations to the Viking aeroshell and to a candidate Jupiter probe are presented and flow fields over these shapes are calculated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1075 , L-11770
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  • 86
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    Turbulent boundary layers over nonstationary plane boundaries (1978)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Methods of predicting integral parameters and skin friction coefficients of turbulent boundary layers developing over moving ground planes were evaluated. The three methods evaluated were: relative integral parameter method; relative power law method; and modified law of the wall method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-74091 , L-11465
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  • 87
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    CAVE3: A general transient heat transfer computer code utilizing eigenvectors and eigenvalues (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The method of solution is a hybrid analytical numerical technique which utilizes eigenvalues and eigenvectors. The method is inherently stable, permitting large time steps even with the best of conductors with the finest of mesh sizes which can provide a factor of five reduction in machine time compared to conventional explicit finite difference methods when structures with small time constants are analyzed over long time periods. This code will find utility in analyzing hypersonic missile and aircraft structures which fall naturally into this class. The code is a completely general one in that problems involving any geometry, boundary conditions and materials can be analyzed. This is made possible by requiring the user to establish the thermal network conductances between nodes. Dynamic storage allocation is used to minimize core storage requirements. This report is primarily a user's manual for CAVE3 code. Input and output formats are presented and explained. Sample problems are included which illustrate the usage of the code as well as establish the validity and accuracy of the method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145290
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  • 88
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    Influence of wave dispersion on vortex pairing in a jet (1978)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The geometry of large-scale structures in the turbulent mixing layer of a moderate Reynolds number jet is deduced from measurements of the fluctuating pressure in the hydrodynamic near field. The structures are rings of concentrated vorticity that distort with downstream distance until statistical axisymmetry disappears. The rings are spaced quasi-periodically and coalesce with each other, producing larger spacings. Statistical and flow-visualization techniques are applied to free and forced jets over a range of Reynolds numbers from 5000 to 50,000 to demonstrate that rings of a given spacing do not coalesce with each other until they are far enough downstream that the local mixing layer has attained some critical thickness which scales with the wavelength of the vortex pair. Wave dispersion is evaluated as a plausible mechanism for localizing the coalescences. The central feature of the model is the observation that a shear layer is dispersive to wavelengths much longer than its thickness and nondispersive to shorter waves.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics; 89; Dec. 13
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  • 89
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    A systems approach to theoretical fluid mechanics: Fundamentals (1978)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A preliminary application of the underlying principles of the investigator's general system theory to the description and analyses of the fluid flow system is presented. An attempt is made to establish practical models, or elements of the general fluid flow system from the point of view of the general system theory fundamental principles. Results obtained are applied to a simple experimental fluid flow system, as test case, with particular emphasis on the understanding of fluid flow instability, transition and turbulence.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-158014 , ME78-2JCA
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  • 90
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    Characteristics of Mach 10 transitional and turbulent boundary layers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measurements of the mean flow properties of transitional and turbulent boundary layers in helium on 4 deg and 5 deg wedges were made for flows with edge Mach numbers from 9.5 to 11.3, ratios of wall temperature to total temperature of 0.4 to 0.95, and maximum length Reynolds numbers of one hundred million. The data include pitot and total temperature surveys and measurements of heat transfer and surface shear. In addition, with the assumption of local similarity, turbulence quantities such as the mixing length were derived from the mean flow profiles. Low Reynolds number and precursor transition effects were significant factors at these test conditions and were included in finite difference boundary layer predictions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1243 , L-12016
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    Experimental perfect-gas study of expansion-tube flow characteristics (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of an experimental investigation of expansion tube flow characteristics performed with helium test gas and acceleration gas are presented. The use of helium, eliminates complex real gas chemistry in the comparison of measured and predicted flow quantities. The driver gas was unheated helium at a nominal pressure of 33 MN sq m. The quiescent test gas pressure and quiescent acceleration gas pressure were varied from 0.7 to 50 kN/sq m and from 2.5 to 53 N/sq m, respectively. The effects of tube-wall boundary layer growth and finite secondary diaphragm opening time were examined through the variation of the quiescent gas pressures and secondary diaphragm thickness. Optimum operating conditions for helium test gas were also defined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1317 , L-12407
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  • 92
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    Bi-directional, buried-wire skin-friction gage (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A compact, nonobtrusive, bi-directional, skin-friction gage was developed to measure the mean shear stress beneath a three-dimensional boundary layer. The gage works by measuring the heat flux from two orthogonal wires embedded in the surface. Such a gage was constructed and its characteristics were determined for different angles of yaw in a calibration experiment in subsonic flow with a Preston tube used as a standard. Sample gages were then used in a fully three-dimensional turbulent boundary layer on a circular cone at high relative incidence, where there were regimes of favorable and adverse pressure gradients and three-dimensional separation. Both the direction and magnitude of skin friction were then obtained on the cone surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-78531 , A-7637
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  • 93
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    A computational model for the prediction of jet entrainment in the vicinity of nozzle boattails (the BOAT code) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of a computational model (BOAT) for calculating nearfield jet entrainment, and its incorporation in an existing methodology for the prediction of nozzle boattail pressures, is discussed. The model accounts for the detailed turbulence and thermochemical processes occurring in the mixing layer formed between a jet exhaust and surrounding external stream while interfacing with the inviscid exhaust and external flowfield regions in an overlaid, interactive manner. The ability of the BOAT model to analyze simple free shear flows is assessed by comparisons with fundamental laboratory data. The overlaid procedure for incorporating variable pressures into BOAT and the entrainment correction employed to yield an effective plume boundary for the inviscid external flow are demonstrated. This is accomplished via application of BOAT in conjunction with the codes comprising the NASA/LRC patched viscous/inviscid methodology for determining nozzle boattail drag for subsonic/transonic external flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3075
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  • 94
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    A three-dimensional turbulent compressible flow model for ejector and fluted mixers (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A three dimensional finite element computer code was developed to analyze ejector and axisymmetric fluted mixer systems whose flow fields are not significantly influenced by streamwise diffusion effects. A two equation turbulence model was used to make comparisons between theory and data for various flow fields which are components of the ejector system, i.e., (1) turbulent boundary layer in a duct; (2) rectangular nozzle (free jet); (3) axisymmetric nozzle (free jet); (4) hypermixing nozzle (free jet); and (5) plane wall jet. Likewise, comparisons of the code with analytical results and/or other numerical solutions were made for components of the axisymmetric fluted mixer system. These included: (1) developing pipe flow; (2) developing flow in an annular pipe; (3) developing flow in an axisymmetric pipe with conical center body and no fluting and (4) developing fluted pipe flow. Finally, two demonstration cases are presented which show the code's ability to analyze both the ejector and axisymmetric fluted mixers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-159467
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  • 95
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    Critical study of higher order numerical methods for solving the boundary-layer equations (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fourth order box method is presented for calculating numerical solutions to parabolic, partial differential equations in two variables or ordinary differential equations. The method, which is the natural extension of the second order box scheme to fourth order, was demonstrated with application to the incompressible, laminar and turbulent, boundary layer equations. The efficiency of the present method is compared with two point and three point higher order methods, namely, the Keller box scheme with Richardson extrapolation, the method of deferred corrections, a three point spline method, and a modified finite element method. For equivalent accuracy, numerical results show the present method to be more efficient than higher order methods for both laminar and turbulent flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1302 , L-11860
    Format: application/pdf
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  • 96
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    Heat exchanger and method of making (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat exchanger of increased effectiveness is disclosed. A porous metal matrix is disposed in a metal chamber or between walls through which a heat-transfer fluid is directed. The porous metal matrix has internal bonds and is bonded to the chamber in order to remove all thermal contact resistance within the composite structure. Utilization of the invention in a rocket chamber is disclosed as a specific use. Also disclosed is a method of constructing the heat exchanger.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 97
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    Heat exchanger (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat exchanger, as exemplified by a rocket combustion chamber, is constructed by stacking thin metal rings having microsized openings therein at selective locations to form cooling passages defined by an inner wall, an outer wall and fins. Suitable manifolds are provided at each end of the rocket chamber. In addition to the cooling channel openings, coolant feed openings may be formed in each of rings. The coolant feed openings may be nested or positioned within generally U-shaped cooling channel openings. Compression on the stacked rings may be maintained by welds or the like or by bolts extending through the stacked rings.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 98
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    The development of a three-dimensional partially elliptic flow computer program for combustor research (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A three dimensional, partially elliptic, computer program was developed. Without requiring three dimensional computer storage locations for all flow variables, the partially elliptic program is capable of predicting three dimensional combustor flow fields with large downstream effects. The program requires only slight increase of computer storage over the parabolic flow program from which it was developed. A finite difference formulation for a three dimensional, fully elliptic, turbulent, reacting, flow field was derived. Because of the negligible diffusion effects in the main flow direction in a supersonic combustor, the set of finite-difference equations can be reduced to a partially elliptic form. Only the pressure field was governed by an elliptic equation and requires three dimensional storage; all other dependent variables are governed by parabolic equations. A numerical procedure which combines a marching integration scheme with an iterative scheme for solving the elliptic pressure was adopted.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3057
    Format: application/pdf
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  • 99
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    Development of a three-dimensional turbulent duct flow analysis (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for computing three-dimensional turbulent subsonic flow in curved ducts is described. An approximate set of governing equations is given for viscous flows which have a primary flow direction. The derivation is coordinate invariant, and the resulting equations are expressed in terms of tensors. General tube-like coordinates were developed for a general class of geometries applicable to many internal flow problems. The coordinates are then particularized to pipes having superelliptic cross sections whose shape can vary continuously between a circle and a near rectangle. The analysis is applied to a series of relevant aerodynamic problems including transition from nearly square to round pipes and flow through a pipe with an S-shaped bend.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3029
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  • 100
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    Advanced designs for fluid flow visualization (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Research was carried out on existing and new designs for minimally intrusive measurement of flow fields in the Geophysical Fluid Flow Cell and the proposed Atmospheric General Circulation Experiment. The following topics are discussed: (1) identification and removal of foreign particles, (2) search for higher dielectric photochromic solutions, (3) selection of uv light source, (4) analysis of refractive techniques and (5) examination of fresnel lens applicability.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-150863 , SAI-79-762-HU
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