computational fluid dynamic (cfd)

One of the powerful tools for fire investigation is Computational Fluid Dynamics, which has the capability to predict all influential parameters in fire, such as temperature, velocity, pressure, toxic species, and radiation. However, this method requires validation to assess the accuracy of the results. This can be achieved by simulating and comparing the results with experimental data to evaluate the numerical accuracy and examine the validity of the governing models used in the simulation. In this study, the temperature conditions, velocity, and combustion species were investigated and analyzed in the geometry of the fire compartment, by comparing the results of two software, FDS and OpenFOAM. It was observed that both software have similar validation results, although OpenFOAM performs slightly better than FDS. For instance, the temperature and CO2 species results in OpenFOAM have a relative error of 22.4 and 16%, while FDS have a relative error of 24 and 31%.

In this study, the effects of linear and rotational speed of the friction stir welding tool was investigated on the heat generation and distribution at surface and inside of workpiece, material flow and geometry of the welding area of poly methyl methacrylate (PMMA) workpiece. The commercial CFD Fluent 6.4 software was used to simulation of the process with computational fluid dynamic technique. To increase the accuracy of simulation, weld area was modeled as a non-Newtonian fluid with pseudo melt behavior around tool pin. The results of the simulation showed at the higher the proportion of rotational speed to linear speed, the material flow in front of the tool and the welding region became bigger. The maximum temperature and turbulence generated heat and material flow were observed at the advancing side. The simulation results were showed acceptable agreement with experimental results. Based on the studied parameters, the maximum generated heat was of 115° C, the maximum material velocity was 0.24 m/s around tool shoulder and maximum pressure on the workpiece was predicted 9 MPa.

Precise modeling has great importance in systems which are designed to work in transonic regions. The scope of current investigation includes numerical simulation of static aeroelastic phenomena of deformable structures in transonic regimes. Transonic flow brings lots of instabilities for aerodynamic systems. These instabilities bring nonlinearity in flow and structure solvers. Due to improvements in numerical methods and also enhancement in computing technologies, computational costs reduced and high-fidelity simulations are more applicable. Simulations in this paper are done in transonic flow (M = 0.96) on the benchmark wing AGARD 445.6. The procedure includes modal analysis, steady flow simulation and investigation of structure’s elastic behavior. At the first phase, the geometry model is validated by modal analysis with regards to comparison of first four natural frequencies and corresponding mode shapes. Then, a loose or staggered coupling is used to analyze aeroelastic behavior of the wing. In each simulation step, imposed pressure on the surfaces of the wing caused by transonic flow regime, deforms the structure. In the results section, a comparison between imposed pressure coefficients in each step with the existing literature and experimental results are reported. Also, pressure coefficients in each steps are calculated and reported. In this investigation by using multiple steps in one-way fluid-structure analysis, deformations are reduced in each step and as a result, the structure reached its static stability point.

The unsteady rotating force or dipole strength distribution, acting by the fan or propeller on the fluid, is predicted by inverse method. In this method, the far-field acoustic pressures are used in non-cavitating condition. In this paper, the far-field acoustic pressures are obtained from Ffowcs Williams and Hawkings (FW-H) equations using computational fluid dynamic (CFD) in specific hydrophone array and then the unsteady rotating force, acting by the propeller on the fluid, is obtained as the most important sound source in non-cavitating condition. The unsteady rotating forces are extracted using inverse method by analytical code in MATLAB. The correct solution is independence to the optimum select of regularization parameter from transfer function; the transfer function represents relationship between the force coefficients and the far-field acoustic pressure. Therefore, the appropriate range of regularization parameter should be choice in order to an ill-conditioned problem from transfer function is solve. The analytical code is solved for different regularization parameters and then the unsteady rotating forces are obtained for three sections on the blade surface. The inverse method could be used for dipole strength distribution calculation as the most important sound source in non-cavitating condition in order to design the noiseless of marine propeller.