The flow regime in the turbulent near wake of a hemisphere

The work presented is a wind tunnel study of the near wake region behind a hemisphere immersed in three different turbulent boundary layers. In particular, the effect of different boundary layer profiles on the generation and distribution of near wake vorticity and on the mean recirculation region is examined. Visualization of the flow around a hemisphere has been undertaken, using models in a water channel, in order to obtain qualitative information concerning the wake structure.List of symbols C _p pressure coefficient, - D diameter of hemisphere - n vortex shedding frequency - p pressure on model surface - p ₀ static pressure - Re Reynolds number, - St Strouhal number, - U, V, W local mean velocity components - mean freestream velocity inX direction - U ^* shear velocity, - u, v, w velocity fluctuations inX, Y andZ directions - X Cartesian coordinate in longitudinal direction - Y Cartesian coordinate in lateral direction - Z Cartesian coordinate in direction perpendicular to the wall - it* boundary layer displacement thickness, - diameter of model surface roughness - elevation angleI - O boundary layer momentum thickness, - _w wall shearing stress - dynamic viscosity of fluid - density of fluid - streamfunction - _x longitudinal component of vorticity, - _y lateral component of vorticity, - _z vertical component of vorticity, This paper was presented at the Ninth symposium on turbulence, University of Missouri-Rolla, October 1–3, 1984     

A technique for evaluation of three-dimensional behavior in turbulent boundary layers using computer augmented hydrogen bubble-wire flow visualization

A system is described which allows the recreation of the three-dimensional motion and deformation of a single hydrogen bubble time-line in time and space. By digitally interfacing dualview video sequences of a bubble time-line with a computer-aided display system, the Lagrangian motion of the bubble-line can be displayed in any viewing perspective desired. The u and v velocity history of the bubble-line can be rapidly established and displayed for any spanwise location on the recreated pattern. The application of the system to the study of turbulent boundary layer structure in the near-wall region is demonstrated.List of Symbols Reynolds number based on momentum thickness u /v - t⁺ nondimensional time - u shear velocity - u local streamwise velocity, x-direction - u ⁺ nondimensional streamwise velocity - v local normal velocity, -direction - x ⁺ nondimensional coordinate in streamwise direction - ⁺ nondimensional coordinate normal to wall - ₊ ^wire wire nondimensional location of hydrogen bubble-wire normal to wall - z ⁺ nondimensional spanwise coordinate - momentum thickness - v kinematic viscosity - _W wall shear stress     

Comparison of one-dimensional models and a 1-D/2-D model for closed-loop thermosyphons with vertical heat transfer sections

The results of a comparison between traditional one-dimensional (1-D) models and a 1-D/2-D model for closed-loop thermosyphons with vertical heat transfer sections are reported in this paper. Attention is limited to problems in which the flow is laminar. For cases where heat losses from the insulated portions of the loop are negligible,St _m=o, it is shown that traditional 1-D models can significantly overpredict the average fluid velocity in the loop for high power inputs (highGr _m). Local results of two-dimensional numerical simulations in the heated and cooled sections reveal that this discrepancy arises because the 1-D models do not account for mixed-convection effects which distort the velocity and temperature profiles from their fully developed forced convection shapes. Furthermore, for cases whereSt _m o, predictions of heat losses (or gains) produced by the 1-D models are handicapped by inaccuracies in the corresponding temperature predictions inside the loop.

---

Vergleich eindimensionaler Modelle mit einem 1-D/2-D Modell zur Berechnung geschlossener Thermosiphonkreisläufe mit vertikalen Wärmeübergangsabschnitten

Zusammenfassung In dieser Arbeit werden die Ergebnisse eines Vergleichs zwischen traditionellen eindimensionalen (1-D) Modellen und einem 1-D/2-D Modell zur Berechnung geschlossener Thermosiphonkreisläufe mit vertikalen Wärmeübergangsabschnitten mitgeteilt. Die Untersuchung beschränkt sich auf reine Laminarströmungen. In Fällen, wo die Wärmeverluste an den isolierten Abschnitten des Kreislaufs vernachlässigt werden können (St _m=o), zeigt sich, daß traditionelle 1-D Modelle die mittlere Strömungsgeschwindigkeit im Kreislauf bei hohem Leistungseintrag (Gr _m hoch) signifikant überbewerten. Örtliche Ergebnisse zweidimensionaler Simultationsrechnungen für die beheizten bzw. gekühlten Abschnitte zeigen, daß diese Widersprüche im Unvermögen der 1-D Modelle begründet liegen, Mischkonvektionseffekte berücksichtigen zu können. Diese deformieren die reiner Zwangskonvektion in ädaquate Form der Geschwindigkeits- und Temperaturfelder. Ferner leidet im FalleSt _m o die Berechnung von Wärmeverlusten oder -gewinnen nach den 1-D Modellen unter der ungenauen Kenntnis der Temperaturverteilung im Inneren des Kreislaufs.

---

Nomenclature f Fanningfriction factor [= _w/(V ²)/2] - g acceleration due to gravity - Gr _q Grashof number - Gr _m modified Grashof number - L total length of the closedloop - P _w power input - Pr Prandtl number [=C _p/k] - q heat flux - R radius of curvature of the 180° bends, Fig. 1 - Re Reynolds number - Re _ref reference Reynolds number - r _i internal radius of the pipe [=D/2] - St _m modified Stanton number - T area-weighted mean cross-sectional temperature - T _a ambient temperature - T _b bulk temperature - T _w mean wall temperature in the cooled section - U overall heat loss coefficient (W/m–°C) - V average velocity in the loop - V nondimensional average velocity [=V/V _ref] - V _ref reference velocity - X parameter used in Eq. (3) - volumetric thermal expansion - z height difference between the middle of the heated and cooled sections, Fig. 1 - length parameter - dimensionless ambient temperature - modified heat loss coefficient This research was financially supported by the Natural Sciences and Engineering Research Council of Canada, in the form of a Post-Graduate Scholarship granted to M. A. Bernier and through individual operating grants awarded to Prof. B. R. Baliga.     

An asymptotic treatment of the transient development of axisymmetric surface waves

A linearized theory is developed for the derivation of an asymptotic solution of the initial value problem of axisymmetric surface waves in an infinitely deep fluid produced by an arbitrary oscillating pressure distribution. An asymptotic treatment of the problem is presented in detail to obtain the solution for the surface elevation for sufficiently large time. Finally, the main prediction of this analysis for some particular pressure distributions of physical interest is exhibited.Nomenclature R, , Y cylindrical polar coordinates - frequency - g acceleration due to gravity - density of fluid - T time - (R, Y; T) velocity potential - E(R, T) vertical surface elevation - P(R, T) applied surface pressure - r, y nondimensional cylindrical polar coordinates, - p(r, t) nondimensional surface pressure - t nondimensional time, T - (r, y; t) nondimensional velocity potential, - (r, t) nondimensional vertical surface elevation, - (k) Hankel transform of a function p(r) with respect to r - I ₁ transient wave integral - I ₂ steady state wave integral     

Regularity for the stationary Navier-Stokes equations in bounded domain

Let u, p be a weak solution of the stationary Navier-Stokes equations in a bounded domain ^N, 5N . If u, p satisfy the additional conditions

Thermal stresses in rectangular plates

Summary A method of determining the thermal stresses in a flat rectangular isotropic plate of constant thickness with arbitrary temperature distribution in the plane of the plate and with no variation in temperature through the thickness is presented. The thermal stress have been obtained in terms of Fourier series and integrals that satisfy the differential equation and the boundary conditions. Several examples have been presented to show the application of the method.Nomenclature x, y rectangular coordinates - _x, _y direct stresses - _xy shear stress - ø Airy's stress function - E Young's modulus of elasticity - coefficient of thermal expansion - T temperature - ² Laplace operator: - ⁴ biharmonic operator - 2a length of the plate - 2b width of the plate - a/b aspect ratio - a _mr, b_ms, c_nr, d_ns Fourier coefficients defined in equation (6) - _m=m/a m=1, 2, 3, ... _n=n/2a n=1, 3, 5, ... - _r=r/b r=1, 2, 3, ... _s=s/2b s=1, 3, 5, ... - A _m, B_m, C_n, D_n, E_r, F_r, G_s, H_s Fourier coefficients - K _rand L _s Fourier coefficients defined in equation (20) - direct stress at infinity - T ₁(x, y) temperature distribution symmetrical in x and y - T ₂(x, y) temperature distribution symmetrical in x and antisymmetrical in y - T ₃(x, y) temperature distribution antisymmetrical in x and symmetrical in y - T ₄(x, y) temperature distribution antisymmetrical in x and y     

Einfluß der Temperaturabhängigkeit der Stoffwerte auf den Wärmeübergang an der turbulent überströmten ebenen Platte

Zusammenfassung Der Einfluß der Temperaturabhängigkeit der Stoffwerte auf den Wärmeübergang ist zur Zeit noch nicht befriedigend geklärt. Da Messungen des Wärmeübergangs stets mit mehr oder weniger großen Fehlern behaftet sind, und da der Einfluß der Temperaturabhängigkeit für die einzelnen Stoffwerte nicht getrennt untersucht werden kann, ist es experimentell praktisch nicht möglich, Korrekturfaktoren zu bestimmen. Es bleibt daher nur der Versuch, rechnerisch dieses Problem anzugehen, wobei es wichtig ist, Verfahren zu benutzen, die nicht zu lange Rechenzeiten erfordern, um eine große Anzahl von Parameterstudien durchzuführen.In einem früheren Aufsatz [2] wurde die Rechnung bei laminarer Grenzschichtströmung vorgestellt. Gegenstand dieser Arbeit ist die Untersuchung des Einflusses der Temperaturabhängigkeit der Stoffwerte auf den Wärmeübergang bei turbulenter Plattengrenzschicht. Die Ergebnisse der Parameterstudien werden diskutiert und mit den bekannten Stoffwertkorrekturtermen von Zhukauskas [1], Sieder u. Tate [10] und Hufschmidt u. Bruck [11] verglichen.

---

Influence of temperature dependent physical properties on the heat transfer in the turbulent boundary layer of a parallel affluxed flat plate

The influence of temperature dependent properties on the heat transfer is not jet satisfying clarified. Measurements of heat transfer contain more or less great faults, and it is practically not possible to investigate the influence of the temperature dependence for particular physical properties separately. Therefore, the only possibility is to examine this problem numerically. Hereby it is important to use methods which don't require too much computing time in order to study a great number of parameters.In a former article [2] such a numerical method about the calculation of a laminar boundary layer was presented.The object of this paper is the investigation of the influence of temperature dependent properties on the heat transfer in the turbulent boundary layer. The results of the parameter studies will be discussed and compared with the well known correction terms from Zhukauskas [1], Sieder and Tate [10] and Hufschmidt and Brack [11].

---

Bezeichnungen c _p spezifische Wärmekapazität - dimensionslose Stromfunktion - l Mischungsweglänge - Nusseltsche Kennzahl - p Druck - Prandtlsche Kennzahl - turbulentePr-Zahl - Reynoldsche Kennzahl - T Temperatur - u,U Strömungsgeschwindigkeit inx-Richtung - Strömungsgeschwindigkeit iny-Richtung - Wärmeübergangskoeffizient - dimensionslosey-Koordinate - dimensionslose Temperatur - Dichte - dynamische Viskosität - _t , _q turbulente Austauschgrößen - kinematische Viskosität - Wärmeleitfähigkeit Indizes außerhalb der Grenzschicht - w an der Wand Vorgetragen auf der Sitzung des GVC-Fachausschusses Wärme- und Stoffübertragung am 15. 4. 1983 in Lindau     

Analytische NÄherungslösung für die laminare Zweistoff-Grenzschichtströmung lÄngs eines ebenen verdunstenden Flüssigkeitsfilms

Zusammenfassung Die Auslegung eines Filmverdampfers für Brennkammern erfordert die Kenntnis des verdunstenden Massenstroms; dieser wird bestimmt durch den gekoppelten WÄrme- und Stoffübergang in der Strömungsgrenzschicht. Die Ergebnisse numerischer Untersuchungen der Massenstromdichte in laminaren Grenzschichten werden herangezogen, um die Genauigkeit einer einfach auszuwertenden analytischen NÄherungslösung zu überprüfen, wobei verÄnderliche Stoffwerte berücksichtigt werden. Die gute übereinstimmung der analytischen NÄherung mit der numerischen Lösung für Benzol zeigt die allgemeine Brauchbarkeit des Verfahrens.

---

Analytical approximation for the laminar binary boundary-layer flow along a vaporizing liquid layer

For the design of a liquid film vaporizer the knowledge of the vaporizing mass flow is necessary. This is determined by the coupled heat and mass transfer. The results of numerical studies of the mass flow rates in laminar boundary layers are taken to test the accuracy of a simple analytical approximation taking variable transport properties into account. The analytical and numerical results for benzole agree rather well pointing out thereby the general validity of this method.

---

Bezeichnungen c Massenkonzentration - c_p spezifische WÄrme - D₁₂ binÄrer Diffusionskoeffizient - f dimensionslose Stromfunktion - h₁,h₂ Enthalpie der Komponenten - K,^* von der Temperatur abhÄngige Koeffizienten (Gl.(11)) - M Molmasse - m^* Massenstromdichte - p Druck - r VerdampfungswÄrme - T Temperatur - u,v Geschwindigkeitskomponenten - x, y, Y Ortskoordinaten - normierte Konzentration - normierte Temperatur - dynamische ZÄhigkeit - Dichte-ZÄhigkeitsverhÄltnis - WÄrmeleitfÄhigkeit Kennzahlen Prandtl-Zahl - Schmidt-Zahl - Reynoldszahl Indizes o Filmoberseite - u Plattenunterseite - 1 Gas 1 (Benzoldampf) - 2 Gas 2 (Luft) - Au\enrand der Grenzschicht     

Thermal effects in the capillary rheometer

Summary The effect of viscous heating in a capillary rheometer is analysed for a power-law fluid by means of a perturbation expansion based upon a boundary-layer-core structure. This expansion is found to complement the eigenfunction series solution obtained by earlier investigators. A similar analysis is presented for the work-of-expansion effect. These two thermal effects are superimposed together with a third perturbation effect due to the pressure dependence of viscosity.On the basis of the present theory, earlier work in this area is discussed and, in some cases, apparent inaccuracies or inconsistencies are pointed out. A means is indicated for correcting data on the basis of the present theory.

---

Zusammenfassung Es wird der Effekt der Erwärmung einer Potenzflüssigkeit infolge viskoser Reibung in einem Kapillar-Rheometer mittels einer Störungsrechnung untersucht, die auf der Unterteilung der Strömung in eine Grenzschicht und einen Kern basiert. Diese Störungsentwicklung ergänzt eine früher von anderen Autoren gefundene Reihenentwicklung mit Hilfe von Eigenfunktionen. Eine ähnliche Untersuchung wird für die thermische Ausdehnungsarbeit durchgeführt. Diese beiden thermischen Effekte sind zusammen einem dritten Störeffekt superponiert, der von der Druckabhängigkeit der Viskosität herrührt.Aufgrund der vorgelegten Theorie werden verschiedene auf diesem Gebiet früher durchgeführte Arbeiten diskutiert, und es werden in einigen Fällen offensichtliche Ungenauigkeiten und Folgewidrigkeiten aufgedeckt. Schließlich wird eine Methode zur Korrektur von Meßdaten mit Hilfe der vorliegenden Theorie angegeben.

---

Nomenclature a tube radius - b ; evaluated atT ₀ andp = 0 when used in perturbation expansion - C _p specific heat - f - f ^* - h defined by eq. [15] - k thermal conductivity - L tube length - m defined by eq. [8] - m ₀ m(T₀, 0) - n power-law index - p pressure - Pe C _p W a/k Peclet number - Pr C _pa/k Prandtl number - Q volumetric flow rate - Q ₀ unperturbed value ofQ in specified-p formulation - r radial coordinate - Re W a/ _a Reynolds number - T temperature - T ₀ inlet temperature - u radial velocity component - u ₀ 0 unperturbed radial velocity - w axial velocity component - w ₀ /W(1 – ) unperturbed axial velocity - W Q/(a ²) average axial velocity - W ₀ Q ₀/(a ²) - z axial coordinate - (3n + 1)/n - ^* ; evaluated atT ₀ andp = 0 when used in perturbation expansion - 4^1-n - ^* - (n + 1)/n - ... shear rate - 4W/a apparent shear rate - p total pressure drop - T _a W ²/k characteristic temperature difference - T _b total bulk-temperature rise - ^* T - r/a - shear viscosity - _a m₀ - (1 –)/ ^1/3 - —p/z - ₀ ... unperturbed value of - z-averaged value of - µ ^{n + 1}/n - z/(a Pe) - _L L/(a Pe) - mass density - _w shear stress at wall - streamfunction - ^*T₀ (absolute temperature scale) - ( )₁ leading-order effect due to viscous heating - ( ) ₁ ^* leading-order effect due to work-of-expansion Note: in specified-p formulation,W gets replaced byW ₀ in definition of Pe, Re, and. With 7 figures and 7 tables     

Rayleigh problem in slip flow with transverse magnetic field

An analytical continuum solution of the Rayleigh problem in slip flow with applied magnetic field is obtained using a modified initial condition and slip boundary conditions. The results are uniformly valid for all times and show that the velocity slip and the local skin friction coefficient remain almost unaffected by the imposition of the magnetic field for small times. They increase however with the magnetic field for large times. The present results reduce to the corresponding results of the hydrodynamic case when there is no magnetic field.Nomenclature A constant - b characteristic length - B magnetic field vector - B ₀ magntidue of the applied magnetic field normale to the plate - B _x magnitude of the induced magnetic field parallel to the plate - C slip coefficient, (2–f)/f - C _f skin friction coefficient, - C _D average drag coefficient - erfc(_x) complementary error function, - E electric field vector - f Maxwell's reflection coefficient - H _a Hartmann number, (B ₀ ² b ²/)^1/2 - nondimensional magnetic parameter - J current vector - Kn=L/b Knudsen number - L mean free path - M Mach number - p constant parameter - P _m magnetic Prandtl number, Re _m/Re= ₀ - q velocity vector - Re Reynolds number, Ub/ - Re _m magnetic Reynolds number, ₀ Ub - t time - nondimensional time, tU/b - u velocity of the fluid parallel to the plate - nondimensional velocity, u/U - U velocity of the plate - Laplace transform of - x, y coordinates along and normal to the plate respectively - y nondimensional distance, y/b - Z nondimensional parameter, 1/Re ^1/2 Kn - ratio of specific heats - boundary layer thickness - velocity slip - viscosity - ₀ magnetic permeability - kinematic viscosity - nondimensional time parameter, ( /Re)^1/2/Kn - density - electrical conductivity     

The unsteady aerodynamics of a first stage stator vane row

The fundamental unsteady aerodynamics on a vane row of an axial flow research compressor stage are experimentally investigated, demonstrating the effects of airfoil camber and steady loading. In particular, the rotor wake generated unsteady surface pressure distributions on the first stage vane row are quantified over a range of operating conditions. These cambered airfoil unsteady data are correlated with predictions from a flat plate cascade inviscid flow model. At the design point, the unsteady pressure difference coefficient data exhibit good correlation with the nonseparated predictions, with the aerodynamic phase lag data exhibiting fair trendwise correlation. The quantitative phase lag differences are associated with the camber of the airfoil. An aft suction surface flow separation region is indicated by the steady state surface static pressure data as the aerodynamic loading is increased. This separation affects the increased incidence angle unsteady pressure data.List of symbols b airfoil semi-chord - C airfoil chord - C _p dynamic pressure coefficient, - _p static pressure coefficient, - i incidence angle - k reduced frequency, - N number of rotor revolutions - p dynamic pressure difference - static pressure difference, - S stator vane circumferential spacing - U _t rotor blade tip speed - u longitudinal perturbation velocity - V absolute velocity - V _axial absolute axial velocity - v transverse perturbation velocity - x _sep location of separation point - inlet angle - inlet air density - blade passing angular frequency     

Turbulent wall pressure fluctuations over wavy surfaces

Measurements of the spectral characteristics of the wall pressure fluctuations produced by a turbulent boundary layer flow over solid sinusoidal surfaces of moderate wave amplitude to wave-length ratios have been obtained. The wave amplitudes were sufficiently small so that the flow remained attatched. The results show that the root mean square pressure level reaches a maximum on the adverse pressure gradient side of the wave at a position somewhat before the trough. Spectral analysis of the pressure fluctuations in narrow frequency bands reveals considerable differences in low and high frequency behavior. At low frequencies, the peak fluctuation amplitude was found at the trough whereas at high frequencies, the peak occurs just after the crest and a minimum is found at the trough. Pressure fluctuations having streamwise correlation lengths on the order of or larger than the wavelength of the surface do not return to their equilibrium (crest) amplitudes as they travel the length of a wave. Pressure fluctuations having streamwise correlation lengths about one order of magnitude less than a wavelength return exactly to their equilibrium amplitudes. Two-point correlation measurements show a decrease in longitudinal coherence on the adverse pressure gradient side of the wave at low frequencies and a considerable increase over a broad frequency range on the positive pressure gradient side. No change is found in the lateral coherence.List of symbols C _f skin friction coefficient - C _p pressure coefficient - C _n Fourier amplitudes of the pressure coefficient - C _dp pressure drag coefficient - d pinhole diameter - f frequency - h half the crest to trough distance - h ₊ nondimensional wave amplitude = - k _n wavenumber = - k fundamental wavenumber = - l _p pressure correlation length - p _s mean surface pressure - P ambient pressure - p fluctuating pressure - p ² mean square pressure - q dynamic head = 1/2 U ² - R space-time correlation - P Reynolds number based on wavelength = - R Reynolds number based on momentum thickness = - t time - R free stream velocity - U mean streamwise velocity - U _e streamwise velocity at the edge of the boundary layer - u ^* friction velocity = - x streamwise coordinate - y wall-normal coordinate - z spanwise coordinate - ⁺ non-dimensional wavelength = ^*) - phase of the cross-spectral density - ^* boundary layer displacement thickness - _long longitudinal coherency - _lat lateral coherency - wavelength of wavy surface - v kinematic viscosity - radian frequency = 2 f - spectral or cross-spectral density - _n phase of the Fourier series - density - time delay - _w wall shear stress - boundary layer momentum thickness     

An analytical solution for the temperature profiles during injection molding,including dissipation effects

An analytical solution is obtained for the stationary temperature profile in a polymeric melt flowing into a cold cavity, which also takes into account viscous heating effects. The solution is valid for the injection stage of the molding process. Although the analytical solution is only possible after making several (at first sight) rather stringent assumptions, the calculated temperature field turns out to give a fair agreement with a numerical, more realistic approach. Approximate functions were derived for both the dissipation-independent and the dissipation-dependent parts which greatly facilitate the temperature calculations. In particular, a closed-form expression is derived for the position where the maximum temperature occurs and for the thickness of the solidified layer.The expression for the temperature field is a special case of the solution of the diffusion equation with variable coefficients and a source term.Nomenclature a thermal diffusivity [m²/s] - c specific heat [J/kg K] - D channel half-height [m] - L channel length [m] - m 1/ - P pressure [Pa] - T temperature [°C] - T _W wall temperature [°C] - T _i injection temperature [°C] - T _A Br independent part of T - T _B Br dependent part of T - T ^core asymptotic temperature - v _z() axial velocity [m/s] - W channel width [m] - x cross-channel direction [m] - z axial coordinate [m] - (x) gamma function - (a, x) incomplete gamma function - M(a, b, x) Kummer function - small parameter - () temperature function - thermal conductivity [W/mK] - viscosity [Pa · s] - ₀ consistency index - power-law exponent - density [kg/m] - similarity variable Dimensionless variables Br Brinkman number - Gz Graetz number -      

Unsteady forces on circular cylinders in a cross-flow

A three-axis piezoelectric load cell was used to measure the local unsteady forces induced on cylinders placed in a cross-flow. In conjunction with this, a single hot-wire was used to traverse the wake at a fixed distance behind the cylinder so that correlations between the induced forces on the cylinder and the wake velocity could be calculated to provide insight into the character of the flow-induced unsteady forces. Experiments were carried out on both two-dimensional and finite-span cylinders at a Reynolds number of 46,000. For the two-dimensional cylinder case, substantial evidence was obtained to demonstrate that the strength of the vortex roll-up along the span was quite uniform. Consequently, the lift-velocity correlation along the span remained unchanged. On the other hand, there was a total lack of correlation between the fluctuating drag and the wake velocity, thus indicating that the drag signal was not quite periodic. In the finite-span cylinder case, the separated flow from the top edge of the cylinder was found to suppress vortex shedding along the span of the cylinder, destroyed its coherence and caused the wake flow to oscillate in the stream direction. This oscillation induced a significant fluctuating drag on the cylinder. Consequently, the fluctuating drag far exceeded the fluctuating lift and the wake velocity was found to correlate well with the drag and not with the lift. This correlation remained intact along the span of the cylinder. Finally, the rms fluctuating lift and drag forces were found to vary along the cylinder span, with the lift increasing and the drag decreasing as the base of the cylinder is approached; thus suggesting that a submerged two-dimensional region exists near the base of the cylinder.List of symbols a span of active element on cylinder - C _D local rms drag coefficient, - C _L local rms lift coefficient, - C _D local mean drag coefficient - (C _D ) _2D spanwise-averaged mean drag coefficient for two dimensional cylinder - d diameter of cylinder (= 10.2 cm) - D fluctuating component of instantaneous drag - D local rms of fluctuating drag - E _D power spectrum of fluctuating drag, defined as - E _L power spectrum of fluctuating lift, defined as - E _U power spectrum of fluctuating streamwise velocity, defined as - f _L dominant frequency of lift spectrum - f _D dominant frequency of drag spectrum - f _u dominant frequency of velocity spectrum - h span of cylinder - H height of test section (= 30.5 cm) - L fluctuating component of instantaneous lift - L local rms of fluctuating lift - R _Du () cross-correlation function of streamwise velocity and local drag - R _Lu () cross-correlation function of streamwise velocity and local lift - Re Reynolds number, - S _L Strouhal number based on f _L , - S _D Strouhal number based on f _D , - S _U Strouhal number based on f _u , - t time - u fluctuating component of instantaneous streamwise velocity - u rms of streamwise fluctuating velocity - u rms of streamwise fluctuating velocity upstream of cylinder - U mean streamwise velocity - U mean stream velocity upstream of cylinder - x streamwise distance measured from axis of cylinder - y transverse distance measured from axis of cylinder - z spanwise distance measured from floor of test section - v kinematic viscosity of air - density of air - time lag in cross-correlation function - _D normalized spectrum of fluctuating drag - _L normalized spectrum of fluctuating lift - _U normalized spectrum of fluctuating streamwise velocity     

LDV measurements of a turbulent air-solid two-phase flow in a 90° bend

Simultaneous measurements of the mean streamwise and radial velocities and the associated Reynolds stresses were made in an air-solid two-phase flow in a square sectioned (10×10 cm) 90° vertical to horizontal bend using laser Doppler velocimetry. The gas phase measurements were performed in the absence of solid particles. The radius ratio of the bend was 1.76. The results are presented for two different Reynolds numbers, 2.2×10⁵ and 3.47×10⁵, corresponding to mass ratios of 1.5×10^–4 and 9.5×10^–5, respectively. Glass spheres 50 and 100 m in diameter were employed to represent the solid phase. The measurements of the gas and solid phase were performed separately. The streamwise velocity profiles for the gas and the solids crossed over near the outer wall with the solids having the higher speed near the wall. The solid velocity profiles were quite flat. Higher negative slip velocities are observed for the 100 m particles than those for the 50 gm particles. At angular displacement =0°, the radial velocity is directed towards the inner wall for both the 50 and 100 m particles. At =30° and 45°, particle wall collisions cause a clear change in the radial velocity of the solids in the region close to the outer wall. The 100 m particle trajectories are very close to being straight lines. Most of the particle wall collisions occur between the =30° and 60° stations. The level of turbulence of the solids was higher than that of the air.List of symbols D hydraulic diameter (100 mm) - De Dean number,De = - mass flow rate - number of particles per second (detected by the probe volume) - r radial coordinate direction - r _i radius of curvature of the inner wall - r ₀ radius of curvature of the outer wall - r ^* normalized radial coordinate, - R mean radius of curvature - Re Reynolds number, - R _r radius ratio, - U ,U _z mean streamwise velocity - U _r ,U _y mean radial velocity - U _b bulk velocity - , _z rms fluctuating streamwise velocity - _r , _y rms fluctuating radial velocity - -r shear stress component - z-y shear stress component - x spanwise coordinate direction - x ^* normalized spanwise coordinate, - y radial coordinate direction in straight ducts - y ^* normalized radial coordinate in straight ducts, - z streamwise coordinate direction in straight ducts - z ^* normalized streamwise coordinate in straight ducts, Greek symbols streamwise coordinate direction - kinematic viscosity of air     

Laminar source flow between parallel porous disks with equal suction and injection

An analysis is presented for laminar source flow between parallel stationary porous disks with suction at one of the disks and equal injection at the other. The solution is in the form of an infinite series expansion about the solution at infinite radius, and is valid for all suction and injection rates. Expressions for the velocity, pressure, and shear stress are presented and the effect of the cross flow is discussed.Nomenclature a distance between disks - A, B, ..., J functions of R _w only - F static pressure - p dimensionless static pressure, p(a ²/ ²) - Q volumetric flow rate of the source - r radial coordinate - r dimensionless radial coordinate, r/a - R radial coordinate of a point in the flow region - R dimensionless radial coordinate of a point in the flow region, R - Re source Reynolds number, Q/2a - R _w wall Reynolds number, Va/ - reduced Reynolds number, Re/r ² - critical Reynolds number - velocity component in radial direction - u dimensionless velocity component in radial direction, a/ - average radial velocity, Q/2a - u dimensionless average radial velocity, Re/r - ratio of radial velocity to average radial velocity, u/u - velocity component in axial direction - v dimensionless velocity component in axial direction, v - V magnitude of suction or injection velocity - z axial coordinate - z dimensionless axial coordinate, z a - viscosity - density - kinematic viscosity, / - shear stress at lower disk - shear stress at upper disk - ₀ dimensionless shear stress at lower disk, - ₁ dimensionless shear stress at upper disk, - dimensionless stream function     

On the operator of symmetric differentiation on a compact Riemannian manifold with boundary

We state a particular case of one of the theorems which we shall prove. Let Ω be a bounded open set in ℝ ⁿ with smooth boundary and let σ=(σ _ij )be a symmetric second-order tensor with components σ _ij εH ^k(Ω) for some (positive or negative) integer k; H ^k are Sobolev spaces on Ω. Then we have for some u _i εH ^k +1(Ω),i=1,...,n, if and only if (if k<0, the integral is in fact a duality) for any symmetric tensor (ω with components and such that ). Some applications in the theory of elasticity are also given.     

Nonlinear Taylor stability of viscoelastic fluids

Using Stuart's energy method, the torque on the inner cylinder, for a second order fluid, in the supercritical regime is calculated. It is found that when the second normal stress difference is negative, the flow is more stable than for a Newtonian fluid and the torque is reduced. If the second normal stress difference is positive, then the flow is more stable and there is no torque reduction. Experimental data related to the present work are discussed.Nomenclature a amplitude of the fundamentals - A _ij ⁽¹⁾ , A _ij ⁽²⁾ first and second Rivlin-Ericksen tensors - d r ₂–r ₁ - D d/dx - E - F - g _ij metric tensor - G torque on the inner cylinder in the supercritical regime - h height of the cylinders - k ₀ /d ² - k ₁ /d ² - I ₁ - I ₂ - I ₃ - I ₄ - r ₁, r ₂ radii of inner and outer cylinders respectively - r ₀ 1/2(r ₁+r ₂) - R Reynolds number ₁ r ₁ d/ ₀ - R _c critical Reynolds number - T Taylor number r _{1 1} ² d ^{3 2}/ ₀ ² *) - T _c critical Taylor number - u ₁, v ₁, w ₁ Fundamentals of the disturbance - u _i , v _i , w _i , (i>1) harmonics - mean velocity (not laminar velocity) - u –u ₁/ar _{1 1} - v v ₁/Rar _{1 1} - x (r–r ₀)/d - , material constants - 0 viscosity - wave number d - density - ₁ angular velocity of inner cylinder - tilde denotes complex conjugate     

Absorption von binären Gasblasen in einer Flüssigkeit mit unterschiedlicher Löslichkeit für die Gaskomponenten

Zusammenfassung Es wird die Absorption einer Einzelblase betrachtet, die aus zwei Gasen A und B besteht, wobei die Flüssigkeit in der Umgebung der Blase A und B in konstanten Konzentrationen enthält.Unter vereinfachten Bedingungen wird das gekoppelte System der Komponentenkontinuitätsgleichungen der Stoffe A und B in der näheren Umgebung der Blase numerisch gelöst. Es werden ausschließlich Fälle betrachtet, in welchen A sehr viel löslicher als B ist.Es stellt sich heraus, daß der Molenbruch an A in der Blase nach einem Anlauf einem stationären Wert zustrebt, der in der Regel nahe am Gleichgewichtswert für A liegt. Wenn dieser stationäre Wert erreicht ist, nimmt die Blasenoberfläche mit konstanter Geschwindigkeit ab oder zu, wobei diese Geschwindigkeit wesentlich von der Löslichkeit von B abhängt.Anhand einiger Beispiele wird dargestellt, in welcher Weise die Verläufe von Blasendurchmesser und-inhalt von den Stoffwerten und den Umgebungs- und Anfangsbedingungen abhängen.

---

Absorption of a single two-component-bubble into liquid

The absorption of a single two-component-gas bubble is considered, the liquid in the vicinity of the bubble containing both gases A and B with constant concentrations. The system of the component continuity equations for A and B in the vicinity of the bubble is solved numerically under simplified conditions. The solubility of A is supposed to be much more important than that of B.It appears, that the mole fraction of A in the bubble tends towards a steady state value which is near its equilibrium value. When this steady state composition is established, the rate of variation of the bubble area becomes constant and depends mainly on the solubility of the less soluble gas B.Some examples show the influence of physical properties, boundary and initial conditions on the variation of the bubble diameter and composition with time.

---

Bezeichnungen d Durchmesser - p_i Partialdruck der Komponente i - p Gesamtdruck - r Radialkoordinate - r*=r/R dimensionslose Radialkoordinate - t Zeit - x_i Molenbruch von i in der Flüssigkeit - x _i ^* Sättigungsmolenbruch von i - y_i Molenbruch von i in der Blase - y _i ^* Molenbruch von i in der Blase, der mit im Gleichgewicht stünde - Fourier-Zahl - H_i Henry-Koeffizient für i - R Blasen-Radius - R₀ Anfangsblasenradius - R*=R/R₀ -- - R_außen äußerer Radius der Grenzschicht - Sh Sherwood-Zahl - -- - -- - _Li Diffusionskoeffizient von i in der Flüssigkeit - -- - Molardichte Indices außerhalb der Grenzschicht - A leichter lösliches Gas - B schwerer lösliches Gas - G Gas - L Flüssigkeit     

Elastohydrodynamic lubrication in a plane slider bearing

Summary The present work deals with the case of a two-dimensional slider bearing with a rigid pad and an elastic bearing. Fluid viscosity is assumed to be only a pressure function. We determined the bearing deformation, the pressure distribution and the load capacity at different values of the inclination angle of the slider, with a numerical integration of the system consisting of the elasticity and Reynolds equations. The results show that, with an iso-viscous fluid, bearing elasticity causes a load capacity decrease. Instead bearing elasticity together with the variation of fluid viscosity due to pressure causes a load capacity greater than that of the iso-viscous case (=0).

---

Sommario Il presente lavoro studia il problema della coppia prismatica lubrificata con pattino rigido di allungamento infinito e cuscinetto deformabile; si suppone che la viscosità del fluido sia funzione della sola pressione. Il sistema di equazioni, costituito dall'equazione di Reynolds e dall'equazione dell'elasticità, è stato risolto numericamente, determinando la deformazione del cuscinetto, andamento della pressione e la capacità di carico per diversi valori dell'inclinazione del pattino. I risultati dimostrano che, con fluido isoviscoso, la deformabilità del cuscinetto determina una riduzione della capacità di carico. Se si considera, invece, effetto combinato dell'elasticità del cuscinetto e della variazione della viscosità del fluido, la capacità di carico risulta maggiore di quella che si ottiene con fluido isoviscoso (=0).

---

Nomenclature /L - /L - x/L - x/L - - ¯C CZ/h ₁ - E elasticity modulus - h film thickness - H elastic deformation of the bearing - h ₁ minimum film thickness - h ₂ inlet thickness - inclination of the pad - h Z/h ₁ - HZ/h ₁ - L pad length - viscosity - ₀ viscosity with no over-pressure - p over pressure - p P _ec-P _rc where:ec=elastic caserc=rigid case - P h ₁ ² /6₀VL - h ₂/h ₁=1+L/h ₁ - FV bearing velocity - W load capacity per unit width - Wh ₂ ¹ /6₀ VL ² - Z E h ₃ ¹ /12 ₀ VL ² A first version of this paper was presented at the 7th National AIMETA congress, held at Trieste, October 2–5, 1984. This work was supported by C.N.R.