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The transient response of an airfoil to a rapidly deploying spoiler is numerically investigated using the turbulent compressible Navier-Stokes equations in two dimensions. Algebraic Baldwin-Lomax model, Wilcox k- ω model, and SST k- ω turbulence model are used to calculate the unsteady separated flow due to the rapid spoiler deployment. The spoiler motion relative to a stationary airfoil is treated by an overset grid bounded by a Dynamic Domain-Dividing Line which has been devised by the authors. The adverse effects of the spoiler influenced by the spoiler location and the hinge gap are expounded. The numerical results are in reasonably good agreement with the existing experimental data.
A numerical simulation was made to determine the motion of particles in the fluid. The simulation is based on the Eulerian-Lagrangian method. The fluid motion was solved using a PISO-based finite-element method and a k-ε model of turbulence. In the Lagrangian method for the solid phase, the trajectories of particles are calculated by integrating the equations of motion of a single particle, and the collision between particles are taken into account. The influence of particles on the fluid phase is taken into account by introducing source terms in the Eulerian equations govering the fluid flow. It is known as the particle-source-in-cell (PSIC) method. Also, the turbulent effect in the particles and fluid motion is considered. The numerical results were compared with the experiment for a two-phase flow in a vertical pipe.
Numerical investigation of a centrifugal compressor volute having a modified straight conical duct has been made. Three-dimensional Reynolds-Averaged Navier-Stokes equations with k-ε turbulence equation are solved To avoid coordinate singularity at the central axis of the duct, multi-block H-type grid is generated on the circular cross-sections of the volute and stretched toward the solid wall boundary. We obtained numerical results with three different mass flow rates at the volute inlet, namely, with the inlet conditions that give small, medium and large mass flow rates at the outlet of the conical duct. Agreement with the experimental results is observed.
Extracorporeal Shock Wave Therapy (ESWT) is known a very effective clinical treatment against persistent musculo-skeletal pains that do not respond with the conservative medical therapy. In the hydroelctric type ESWT, shock waves are generated by the electric sparks between two electrodes a few milimeters apart charged in tens of thousand volts, immersed in water and located at the first focal point of an ellipsoidal reflector. Then the shock is focused at the second focal point of the reflector for clinical use. The shock wave is bombarded thousand of times on the target area positioned at the second focal point. In this medical equipment, there is lots of obscurity in the physical and biological effect. We first make CFD analysis to expound the shock focusing process of this pressure device.
In this paper, the problem of transonic aerodynamic characteristics of a NACA0012 airfoil is numerically investigated in the inviscid gas-droplet two-phase flow with the compressible two-fluid model. In the present study, the airfoil flight in the cloud is simulated by taking account of the viscous drag of the droplets, the heat transfer, the phase change, and the droplet fragmentation. The two-fluid equation system is solved by the fractional-step method and the WAF-HLL scheme. The effects of size and volume fraction of the droplets on the flow characteristics of the airfoil in the cloud are elaborated and discussed.