Numerical prediction of ship hydrodynamic performance at design stage using computational fluid dynamics (CFD) technique is a most important and challenging subject in the field of ship hydrodynamics.

Numerical prediction of ship hydrodynamic performance using computational fluid dynamics (CFD) technique at design stage is an important and challenging subject in the field of ship hydrodynamics.

Amethod for the estimation of hydrodynamic forces of fin-rudder on slender body of revolution is presented, based on the results of series model tests which were performed to obtain steady and rotary force derivatives.

New nondimensional geometric parameters of fin-rudder are introduced, so that the problem of interaction of hydro-dynamic forces between fin-rudder and main body is well resolved. Based on the wing theory and the orthogonal design method used for the analysis of the results of series model tests, a semi-empirical expression for the determination of hydrodynamic forces of fin-rudder is obtained.

Considering the effect of the bottom on the hydrodynamic properties of the rudder, the authors are discussing with the help of the numerical value test method that the fluid dynamic force of rudder varies with the distance from the ship bottom to the rudder top.

An unsteady nonlinear vortex-lattice method is presented for calcula-tion of hydrodynamic forces acting on the rudder with tip edge separation. The numerical method is applied to three rectangular rudders with aspectratio 2.4,1.0 and 0.211 respectively.

The linearity of calibration curve provided by SEKI was similar to that offered by non-bias hydrodynamic injection (HDI) but significantly better than that obtained by EKI.

Based on hydrodynamic equations, an equation formulizing the parametric instability was derived.

Based on the variational constraint approach, the variational form of Reynolds equation in hydrodynamic lubrication is revised continuously to satisfy certain constraints in the cavitation zone of oil film field.

Method of internal 3D flow field numerical simulation for hydrodynamic torque converter

The performance parameters of the hydrodynamic torque converter were predicted.

The wake model, suggested by T. Y. Wu in 1962, is linearized and applied to treat the two-dimensional supereavitating or partially cavitating hydrofoil of the arbitrary camberline. The rear end of the cavity in this model, which may also be called as" open type model" in the linearized theory, is regarded as nonclosed. At the downstream of the cavity, there is a wake region stretched to the infinity. For a part of the free streamline near the hydrofoil, the pressure is assumed to be constant and equal to the...

The wake model, suggested by T. Y. Wu in 1962, is linearized and applied to treat the two-dimensional supereavitating or partially cavitating hydrofoil of the arbitrary camberline. The rear end of the cavity in this model, which may also be called as" open type model" in the linearized theory, is regarded as nonclosed. At the downstream of the cavity, there is a wake region stretched to the infinity. For a part of the free streamline near the hydrofoil, the pressure is assumed to be constant and equal to the saturated vapor pressure. For the free streamline downward of the former part, the pressure gradually increases and finally reaches the value of that of the infinitely forward undisturbed stream. There exists the wake region and thus the stagnation (point (singular points) is avoided at the rear end of the cavity. The application of this model provides a smooth continuous transition of the solution from the fully eaviteted flow to fully wetted flow. The results, obtained in this paper, may be used to estimate the hydrodynamic forces as a first approximation in the transitional state, for it is commonly known that the result, obtained with the closed model, is invalid, as the cavity length approaehing to that of the chord. Besides, there are only two unkown constants in the author's solution, thus the calculation can be simplified.

In this paper, we have generalized the "Prago-Figiaivsky's" wing theory of small aspect ratio, have established the formulas of the coefficients of normal force, induced resistance and the center of pressure. We have also suggested a way to evaluate the lower limit of the critical angle of attack. After re-calculating the hydrodynamic forces of a rectangular plate, we have applied this method to rudder behind the ship and propeller. Results are in agreement with the known experimental or theoretical results....

In this paper, we have generalized the "Prago-Figiaivsky's" wing theory of small aspect ratio, have established the formulas of the coefficients of normal force, induced resistance and the center of pressure. We have also suggested a way to evaluate the lower limit of the critical angle of attack. After re-calculating the hydrodynamic forces of a rectangular plate, we have applied this method to rudder behind the ship and propeller. Results are in agreement with the known experimental or theoretical results.

When a glider moves in a seaway, it yields oscillations. M. D. Haskind discussed the non-steady motions of small curved planing plate by using the theory of complex functions, and obtained the general expression of hydrodynamic forces. In this paper, the pressure distribution of hydrodynamic forces on the planing plate was obtained with another method. First, in solving a pulsating pressure point δ(x)cos(wt ε) on the free surface, the expressions of its normal induction velocity v(x, t; U, ω, ε)...

When a glider moves in a seaway, it yields oscillations. M. D. Haskind discussed the non-steady motions of small curved planing plate by using the theory of complex functions, and obtained the general expression of hydrodynamic forces. In this paper, the pressure distribution of hydrodynamic forces on the planing plate was obtained with another method. First, in solving a pulsating pressure point δ(x)cos(wt ε) on the free surface, the expressions of its normal induction velocity v(x, t; U, ω, ε) for two cases of β<1/4 and β>1/4 were obtained. Then the planing plate was replaced by an unknown pressure distribution and obtained its induction velocities. By equating the normal induction velocity on the planing plate to its normal velocity of pitching and heaving motions, obtained the integral equations of the unknown pressure distribution. To derive the formulas of heaving force and pitching moment, the integral equations were solved by turned into a system of infinite linear algebraic equations, also the solubility of this system of infinite equations was discussed. Finally, a numerical example for the pressure distribution on the planing plate was calculated by taking its first six-terms of Fourier expansion series.