Allowance for the unsteadiness of the flow in determining the critical cavitation number for marine propellers

A method of estimating the critical cavitation number for marine propeller blades is proposed. This method is based on the reduction of the three-dimensional unsteady problem to the three-dimensional steady problem and a series of two-dimensional unsteady problems.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No.1, pp. 78–85, January–February, 1993.The authors are grateful to S. V. Kaprantsev for assisting with the experiments.     

On the problem of eversion for incompressible elastic materials

The paper contains a discussion on when eversion of cylindrical tubes and spherical shells is possible. The analysis shows that eversion of a cylindrical tube of every isotropic incompressible elastic material with no applied forces is possible assuming only the E-inequalities. This is not always true for spherical shells. Conditions are given as to when this is possible and when it is not possible.     

Further studies on dynamic crack branching

The newly derived dynamic-crack-branching criterion with its modifications is verified by the dynamicphotoelastic results of dynamic crack branchings in thinpolycarbonate, single-edged crack-tension specimens. Successful crack branching was observed in four specimens and unsuccessful branching in another. Crack branching consistently occurred when the necessary conditions ofK _I =K _{I b} =3.3 MPa \(\sqrt m\) and the sufficiency condition ofr _o =r _c =0.75 mm were satisfied simultaneously. In the unsuccessful branching test, the necessary condition was not satisfied sinceK _I was always less thanK _{I b} .     

Efficient implicit algorithm for the equations of 2-D viscous compressible flow: application to shock-boundary layer interaction

A fully implicit algorithm has been developed to time integrate the equations of 2-D compressible viscous flow. The algorithm was constructed so as to optimize computational efficiency. The time-consuming block matrix inversions usually associated with implicit algorithms have been reduced to the trivial non-iterative inversion of four sets of scalar bidiagonal matrices. Thus, the algorithm requires virtually no more computer storage than an explicit algorithm. The efficient structure of the implicit algorithm is reflected in comparative timings which slow that it requires only a factor of two more computer time per point per time step than a typical explicit algorithm. Therefore, the algorithm allows more economical solution of given flows than existing explicit methods and also allows more difficult problems to be attempted using available computer resources. Application of the algorithm to the problem of shock-boundary layer interaction produces results consistent with both experimental measurements and other calculations.     

The effect of hydrogen bubbles on the thymol blue velocity measurement technique

This note describes an experimental study of the damaging effect of hydrogen bubbles on the effectiveness of the thymol blue velocity measurement method. Specifically, we document the effect of flow velocity, cathode voltage, and cathode diameter on bubble formation and the quality of the thymol blue pattern. The time of bubble damage, i.e., the interval preceding the destruction of the blue pattern, was measured and reported as a function of flow velocity, cathode voltage, and cathode diameter.     

Dissipation of the energy of sound waves in small gas bubbles

One of the main factors affecting the dynamics of homogeneous solution type pulse reactors is the formation of gas bubbles on the fission-fragment tracks [1, 2]. The behavior of the reactor depends very considerably on the size (10^?5 cm) and growth rate of these bubbles [2], and it is, accordingly, a very important matter to study these properties. One convenient means of doing this lies in the acoustic method. The behavior of gas bubbles in the field of a sound wave has been studied in a large number of papers and reviews [3, 4]. In this paper we shall see the approximation of a sound wave of small amplitude to consider the dissipation of sound-wave energy in a gas bubble, at the same time allowing for inertia, surface tension, viscosity, heat transfer, and the diffusion of gas through the surface of the bubble.     

Method of calculating the contours of aerodynamic nozzles with transition through the velocity of sound

The existing methods of constructing an “ideal” contour (i.e., a contour without taking account of viscosity) for aerodynamic nozzles has a number of drawbacks: they are extremely unwieldly and are not versatile and, moreover, they give in practice an impairment of the flow uniformity, caused by nonconformity of the true flow in the transonic region assumed in the solution, as only the hypersonic flow region is usually calculated. In this paper, a method is proposed for calculating the ideal contours of aerodynamic nozzles with transition through the velocity of sound, which is free from these drawbacks. Cauchy's problem is solved numerically by the method in [1]. A specially corrected pressure distribution, obtained experimentally [2], is used as the initial distribution. Examples of the calculation are given for the ideal contours of plane, axisymmetrical and annular aerodynamic nozzles.     

Motion of a solitary wave over a submerged ridge

The two- and three-dimensional motion of a stationary wave in a layer of liquid with a variable depth was studied earlier by Grimshaw [1, 2], who showed that if the unperturbed state of the liquid were a state of rest, then a certain integrated quantity characterizing the energy of the wave (referred to one element on the leading edge of the wave) was conserved during the motion. In the present investigation (which is based on this property) we shall establish the shape of the wave front for the case of steady motion over an infinite submerged cylindrical ridge; we shall present a model describing a wave of limiting amplitude and shall consider the transient perturbation of the steady-state solution. We should note that one particular case (the motion of a straight front, orthogonal to the axis of the ridge, in a direction parallel to this axis) was considered by another method in [3].     

Experiments on the postbuckling behavior of circular cylindrical shells under compression

Detailed experimental studies are performed on the postbuckling behavior of circular cylindrical shells under compression, by using polyester test cylinders with the geometric parameterZ ranging from 20 to 1000. In each case, variations of the equilibrium load, circumferential wave number and maximum inward and outward deflections, with applied edge shortenings, are clarified. Contour lines for typical postbuckling configurations are also shown. It is found that, as the cylinder is compressed beyond the primary buckling, secondary bucklings take place successively with diminishing wave numbers, and that postbuckling equilibrium loads become significantly lower than those at buckling asZ increases. Further, for short shells withZ≦100, the buckled waveforms are always symmetric with one-tier diamond buckles, while for longer shells, asymmetric postbuckling patterns with two tiers of buckles dominate.