bluuebunny/crossref_metadata_2025_split huggingface dataset:
Clinicopathologic and Immunohistochemical Study of Intraoral Mucoepidermoid Carcinoma
Authors: Lopes Márcio Ajudarte , da Cruz Perez Danyel Elias , de Abreu Alves Fábio , de Almeida Oslei Paes , Kowalski Luiz Paulo 
Published: March 2006

OBJECTIVEThe purpose of this study is to assess the clinicopathologic and immunohistochemical features of intraoral mucoepidermoid carcinomas and its relationship with the prognosis.STUDY DESIGN AND SETTINGFrom 1953 to 1993, 27 patients with intraoral mucoepidermoid carcinomas surgically treated were selected for this study. Clinical data were obtained from the medical records, the microscopic slides were reviewed, the tumors were graded, and immunohistochemical analysis for p53, PCNA, cerbB‐2, and CEA were carried out.RESULTSThe tumors were more frequent in patients between 40 and 60 years of age (40.7%), without gender predilection. Hard palate was the most common site with 13 cases (48%). T2 was the more frequent stage (48%) and 2 patients (7.4%) were staged as N +. Most tumors (48%) were classified as low grade of malignancy. The expression of PCNA was associated to high‐grade tumors (P =. 00610) and c‐erbB‐2 to low grade tumors (P =. 03958). No recurrence was noted in most of the cases (22 cases, 81.5%). Three cases (11.1%), however, showed local recurrence and 2 patients (7.4%) died because of the disease. The analysis of the overall survival rate showed that male patients (P =. 04249), stage N (P =. 05948), high grade of malignancy (P =. 0009), strong expression of PCNA (P =. 09128), and weak expression of c‐erbB‐2 (P =. 03334) had the lowest survival rates.CONCLUSIONOur results showed that patients with intraoral mucoepidermoid carcinoma had a reduced survival expectation if they were of the male gender, with regional metastasis, high grade of malignancy, strong expression of PCNA and weak expression of c‐erbB‐2.
Histologic Evaluation of Intracordal Autologous Cartilage Injection in the Paralyzed Canine Vocal Fold at Two and Three Years
Authors: Lee Byung‐Joo , Wang Soo‐Geun , Goh Eui‐Kyung , Chon Kyong‐Myong , Lee Chang‐Hun , Lorenz Robert R. 
Published: March 2006

OBJECTIVEIntracordal injection for vocal fold augmentation is easy and simple and does not require a cervical skin incision. We reported previously on the 1‐year results of injected autologous auricular cartilage for volumetric augmentation in paralyzed canine vocal cord. This study evaluates the long‐term histomorphologic results of injected autologous auricular cartilage for the augmentation of the paralyzed canine vocal fold at 2 and 3 years.STUDY DESIGN AND SETTINGA prospective trial of autologous cartilage augmentation of vocal cord in animal model. Five dogs were operated on. A piece of auricular cartilage was harvested from the ear and minced into tiny chips with a scalpel. Fat was harvested from inguinal area and minced with a scalpel. The minced cartilage and fat‐paste (0.2 ml) was injected using a pressure syringe into the paralyzed thyroarytenoid muscle using direct laryngoscopy. Three animals were sacrificed at 2 years, two at 3 years. Each subject underwent laryngectomy and serial coronal sections of paraffin blocks from the posterior vocal fold were made.RESULTSThere was no significant complications perioperatively or postoperatively. The injected cartilage that seemed to have lost viability existed in the vocalis muscles until 36 months. Fibrotic change was exhibited in the surrounding injected cartilage. There were no differences between 2 and 3 years in histomorphologic results of the injected cartilage.CONCLUSIONThe autologous auricular cartilage graft is well tolerated and may be a very effective material for long‐term volumetric augmentation in the paralyzed vocal cord.
DETERMINANTS OF CHRONIC MALNUTRITION AMONG PRESCHOOL CHILDREN IN BANGLADESH
Authors: RAHMAN AZIZUR , CHOWDHURY SOMA 
Published: March 2006

Summary.This study investigated the impact of some socioeconomic, demographic and health and community factors on chronic malnutrition or stunting in Bangladeshi children aged less than 5 years. The analysis revealed that the overall prevalence of stunting was 44%, of which 18% of children were severely stunted, and the demographic characteristics appeared to be the most significant factors for chronic malnutrition. Multinomial logistic regression analysis showed that parents’ education, household economic status, media exposure, number of under-5 children, place of delivery, child’s age, birth order, months of breast-feeding, birth size, mother’s BMI, mother’s height, age of household head, measles vaccine, supplementation of diet with liquids and regional differentials were significantly associated with severe as well as moderate stunting.
The displacement effect of a sphere in a two-dimensional shear flow
Authors: Hall I. M. 
Published: March 2006

This paper contains a theoretical investigation of the displacement effect of a pitot tube in a shear flow. Viscosity is neglected throughout so that the vorticity field alone is considered.It is first shown that a two-dimensional approach does not produce a large enough displacement effect because it does not include the stretching of vortex tubes that takes place around a three-dimensional pitot tube. Then the three-dimensional problem is considered. A solution is obtained in the plane of symmetry for a sphere in a shear flow. This solution is found by making an assumption about the rate of stetching of vortex tubes perpendicular to the plane of symmetry and then considering the shear flow as a small perturbation of a uniform flow. A solution in the plane of symmetry is sufficient to obtain the displacement effect, which is found to be of the same order as the experimental result obtained by Young & Maas (1936) for a conventional pitot tube. The sphere may be considered to represent a conventional pitot tube (of slightly smaller diameter), so it is concluded that a large part of the displacement effect of a pitot tube may be accounted for without the inclusion of viscosity, i.e. by consideration of the vorticity field alone.To a first approximation, the vorticity in the plane of symmetry is found to depend only on the distance from the centre of the sphere.An outline of shear flows past some two-dimensional bodies is given in an appendix. The bodies considered are a circular cylinder and a two-dimensional ‘pitot-tube’ consisting of two parallel semi-infinite plates.
The law of the wake in the turbulent boundary layer
Authors: Coles Donald 
Published: March 2006

After an extensive survey of mean-velocity profile measurements in various two-dimensional incompressible turbulent boundary-layer flows, it is proposed to represent the profile by a linear combination of two universal functions. One is the well-known law of the wall. The other, called the law of the wake, is characterized by the profile at a point of separation or reattachment. These functions are considered to be established empirically, by a study of the mean-velocity profile, without reference to any hypothetical mechanism of turbulence. Using the resulting complete analytic representation for the mean-velocity field, the shearing-stress field for several flows is computed from the boundary-layer equations and compared with experimental data.The development of a turbulent boundary layer is ultimately interpreted in terms of an equivalent wake profile, which supposedly represents the large-eddy structure and is a consequence of the constraint provided by inertia. This equivalent wake profile is modified by the presence of a wall, at which a further constraint is provided by viscosity. The wall constraint, although it penetrates the entire boundary layer, is manifested chiefly in the sublayer flow and in the logarithmic profile near the wall.Finally, it is suggested that yawed or three-dimensional flows may be usefully represented by the same two universal functions, considered as vector rather than scalar quantities. If the wall component is defined to be in the direction of the surface shearing stress, then the wake component, at least in the few cases studied, is found to be very nearly parallel to the gradient of the pressure.
On the propagation of weak shock waves
Authors: Whitham G. B. 
Published: March 2006

A method is presented for treating problems of the propagation and ultimate decay of the shocks produced by explosions and by bodies in supersonic flight. The theory is restricted to weak shocks, but is of quite general application within that limitation. In the author's earlier work on this subject (Whitham 1952), only problems having directional symmetry were considered; thus, steady supersonic flow past an axisymmetrical body was a typical example. The present paper extends the method to problems lacking such symmetry. The main step required in the extension is described in the introduction and the general theory is completed in §2; the remainder of the paper is devoted to applications of the theory in specific cases.First, in §3, the problem of the outward propagation of spherical shocks is reconsidered since it provides the simplest illustration of the ideas developed in §2. Then, in §4, the theory is applied to a model of an unsymmetrical explosion. In §5, a brief outline is given of the theory developed by Rao (1956) for the application to a supersonic projectile moving with varying speed and direction. Examples of steady supersonic flow past unsymmetrical bodies are discussed in §6 and 7. The first is the flow past a flat plate delta wing at small incidence to the stream, with leading edges swept inside the Mach cone; the results agree with those previously found by Lighthill (1949) in his work on shocks in cone field problems, and this provides a valuable check on the theory. The second application in steady supersonic flow is to the problem of a thin wing having a finite curved leading edge. It is found that in any given direction the shock from the leading edge ultimately decays exactly as for the bow shock on a body of revolution; the equivalent body of revolution for any direction is determined in terms of the thickness distribution of the wing and varies with the direction chosen. Finally in §8, the wave drag on the wing is calculated from the rate of dissipation of energy by the shocks. The drag is found to be the mean of the drags on the equivalent bodies of revolution for the different directions.
Supersonic flow past a bluff body with a detached shock Part I Two-dimensional body
Authors: Chester W. 
Published: March 2006

The flow at high Mach number past a body with a rounded nose is considered. Viscosity and heat conduction are neglected, and the body is assumed to be two-dimensional and symmetrical about an axis parallel to the incident stream.An exact solution is first obtained in the case λ → 1, M → ∞, where λ is the adiabatic index and M is the Mach number. This solution is then used as the basis of a double expansion in δ = (λ - 1)/(λ + 1) and M−2, after the exact solution has been modified to make the series expansion converge near the body. The expansion is carried out as far as the terms of order (δ + M−2)2.The results are displayed for various values of δ and M−2; typical results are as follows. With M−2 = 0, δ = 1/6 (λ = 1.4), and for a parabolic body having unit radius of curvature at the nose, the shock is approximately a parabola with radius of curvature 1.822 at the nose. The distance between the body and the shock along the axis of symmetry is 0.323, and the height of the sonic point from this axis is 0.744 both on the shock and on the body. The actual pressure distribution on the body is shown in figure 4, and agrees well with experiment. The pressure falls to zero at a distance 0.86 downstream from the nose of the body, measured along the axis of symmetry. On the assumption that the pressure remains negligible beyond this point, the total drag is 1.39 ρV2, where ρ0 is the density andV is the velocity of the incident stream.
The refraction of shock waves at a gaseous interface
Authors: Jahn Robert G. 
Published: March 2006

A programme of shock tube experiments has been conducted to study the refraction of plane shock waves at interfaces between two gases. Shocks of strength ζ = 0·85 (weak) and ζ = 0·30 (fairly strong) were allowed to impinge, at various angles of incidence, on interfaces between air/CO2and air/CH4, and the resulting configurations were photographed through a Mach-Zehnder interferometer. From the interferograms, measurements were made of the strengths of the reflected waves, and of the angles of refraction, and the values were compared with the theoretical calculations of Polachek & Seeger (1951). Within the range of parameters for which the refraction model assumed by the theory is applicable–the so-called ‘regular refraction’ region–the observations were in excellent agreement with the theoretical predictions.When the study was extended to ranges of the parameters for which the theory is clearly inadequate, a succession of rather complex ‘irregular refraction’ patterns was observed. Although these configurations were highly interesting qualitatively, each of them involved curved shocks, non-uniform regions of flow, and other less simple processes which discouraged any formal theoretical analysis. On a less rigorous basis, however, it could be shown that these patterns were internally consistent, and that each represented a distortion of a regular refraction process which was reasonable under the prevailing aerodynamic conditions.Certain observations in these refraction experiments appear to be of some significance outside the specific problem. (i) The sensitivity of strong shock refractions to the values of the specific heat ratio λ for the two gases suggests a possible technique for the measurement of λ and its temperature dependence. (ii) Two of the irregular refraction patterns display a transition process which would be equally appropriate to the onset of the Mach configuration in the shock reflection problem. (iii) Some irregular refractions can be considered as special cases in the problem of the interaction of a shock and a boundary layer.
Supersonic flow past a bluff body with a detached shock Part II Axisymmetrical body
Authors: Chester W. 
Published: March 2006

This paper considers the flow at high Mach number behind the curved shock formed when a supersonic stream impinges on an axisymmetrical body with a rounded nose.The solution is obtained as a double expansion in
$\delta = (\gamma -1)|(\gamma +1),$
where γ is the adiabatic index, and M−2; the expansion is developed to within terms of order (δ+M−2)3.Expressions are obtained for the distance between the body and the shock, the radius of curvature of the shock compared with that of the body, and the pressure distribution on the body.
On the motion of small spheroidal particles in a viscous liquid
Authors: Saffman P. G. 
Published: March 2006

Small spheroidal particles suspended in a sheared viscous liquid are sometimes observed to take up slowly preferred orientations, relative to the motion of the undisturbed liquid, which are independent of the initial conditions of release. These obsevations cannot be accounted for by the solution, obtained by Jeffery (1922), of the linearized Navier-Stokes equations. It is shown in this paper that the effect of the inertia of the liquid is to alter slowly the orbit of the particle in accordance with Jeffery's hypothesis that the particle ultimately moves in such a way that the dissipation of energy is a minimum, but that this effect is orders of magnitude too small to account for any of the experimental observations.It is suggested that non-Newtonian properties of the liquid account for the observations. It is shown that the rate of orientation of a particle would then be independent of its size, and this prediction is verified experimentally. Other experimental evidence in support of this suggestion is also described.Some remarks are also made about the possible effect of collisions between the particles when more than one particle is present.
A new approach to problems of shock dynamics Part I Two-dimensional problems
Authors: Whitham G. B. 
Published: March 2006

In this paper, two-dimensional problems of the diffraction and stability of shock waves are investigated using an approximate theory in which disturbances to the flow are treated as a wave propagation on the shocks. These waves carry changes in the slope and the Mach number of the shock. The equations governing the wave propagation are analogous in every way to the non-linear equations for plane waves in gas dynamics, and their solutions can be deduced by the same mathematical techniques. Since the propagation speed of the waves is found to be an increasing function of Mach number, waves carrying an increase in Mach number will eventually break and form what we may call a ‘shock’, corresponding to the breaking of a compression wave into a shock in the ordinary plane wave case. Such a ‘shock’ moving on the shock is called ashock-shock.The shock-shock is a discontinuity in Mach number and shock slope, and it must be fitted in to satisfy the appropriate relations between these are interpreted as the trace of cylindrical sound waves in the flow behind the shock. In particular a shock-shock is the trace of a genuine shock in the flow behind, and thus corresponds to Mach reflection.The general theory of the wave propagation is set out in § 2. The subsequent sections contain applications of the theory to specific problems, including the motion of a shock along a curved wall, diffraction by a wedge, stability of plane shocks and the instability of a converging cylindrical shock.
Expansions at small Reynolds numbers for the flow past a sphere and a circular cylinder
Authors: Proudman Ian , Pearson J. R. A. 
Published: March 2006

This paper is concerned with the problem of obtaining higher approximations to the flow past a sphere and a circular cylinder than those represented by the well-known solutions of Stokes and Oseen. Since the perturbation theory arising from the consideration of small non-zero Reynolds numbers is a singular one, the problem is largely that of devising suitable techniques for taking this singularity into account when expanding the solution for small Reynolds numbers.The technique adopted is as follows. Separate, locally valid (in general), expansions of the stream function are developed for the regions close to, and far from, the obstacle. Reasons are presented for believing that these ‘Stokes’ and ‘Oseen’ expansions are, respectively, of the forms
$\Sigma \;f_n(R) \psi_n(r, \theta)$ and $\Sigma \; F_n(R) \Psi_n(R_r, \theta)$
where (r, θ) are spherical or cylindrical polar coordinates made dimensionless with the radius of the obstacle, R is the Reynolds number, and $f_{(n+1)}|f_n$ and $F_{n+1}|F_n$ vanish with R. Substitution of these expansions in the Navier-Stokes equation then yields a set of differential equations for the coefficients ψn and Ψn, but only one set of physical boundary conditions is applicable to each expansion (the no-slip conditions for the Stokes expansion, and the uniform-stream condition for the Oseen expansion) so that unique solutions cannot be derived immediately. However, the fact that the two expansions are (in principle) both derived from the same exact solution leads to a ‘matching’ procedure which yields further boundary conditions for each expansion. It is thus possible to determine alternately successive terms in each expansion.The leading terms of the expansions are shown to be closely related to the original solutions of Stokes and Oseen, and detailed results for some further terms are obtained.
Steady state free thermal convection of liquid in a saturated permeable medium
Authors: Wooding R. A. 
Published: March 2006

The partial differential equations which describe steady flow of fluid in saturated homogeneous permeable solid material under non-isothermal conditions are stated. From these are derived the equations for flow of liquid (in particular, water) using suitable approximations and making use of empirical laws when necessary.It is then postulated that the only ‘ponderomotive’ (i.e. massmoving) forces present are those due to thermal expansion effects. Free convection results. An approximate solution of the equations is attempted for plane flow by means of classical perturbation methods, the temperature and stream-function variables being represented by power series in a convection parameter proportional to the Rayleigh number.A numberical example of the method, with boundary conditions based on a geothermal area at Wairakei, New Zealand, is given. The results show features which are in fair agreement with temperature measurements made in the area, and it appears that the convection parameter η is of the order of 10.
The motion of a shock wave in a channel, with applications to cylindrical and spherical shock waves
Authors: Chisnell R. F. 
Published: March 2006

A first-order relationship between changes in area and shock strength is derived for the case of a shock moving through a small area change in a channel. By integration of this relationship the area of the channel is obtained as a function of the shock strength in closed form. This result is interpreted as giving the average strength of a shock at a given time as it moves along a channel of arbitrary shape.By suitable choices of the shape of the channel, descriptions of converging cylindrical and spherical shocks are obtained. These descriptions are found to be in close agreement with the similarity solutions valid near the points of collapse of the shocks. The reason for such good agreement is examined.
Oscillations of tide and surge in an estuary of finite length
Authors: Proudman J. 
Published: March 2006

This paper concerns a narrow basin of uniform cross-section open to the sea at one end and closed at the other. An incident long wave of prescribed general form is supposed to enter from the sea and to represent the combination of tide and surge as generated in the sea. The solution of the linear terms of the equations of continuity and motion gives the reflection of this wave at the head of the estuary. This paper gives the next approximation when the non-linear terms are retained, the second-order motion being made determinate by the condition that, at the mouth, it reduces to a progression towards the sea.The chief results relate to the surface elevation at the head of the estuary. When the first order elevation there increases steadily to a maximum, the effect of the ‘shallow water terms’ is to make high water higher and earlier, while the effect of the ‘frictional term’ is to make high water lower and later. For a short estuary, the interaction of the tide on a surge, due to a given sequence of meteorological conditions over the sea, is to make it higher when its maximum occurs at the time of tidal high water than when its maximum occurs at the time of tidal low water. This is directly opposite to the corresponding result when the estuary is of infinite length.