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This work aims to prediction of laminar/turbulent transition which plays an important role on aerodynamics of wing section. In this respect the flow around the NACA2415 airfoil simulated in a Computational Fluid Dynamics (CFD) solver in different regimes with and without propeller flowfield. For predicting the transition onset, two approaches were used: The first is based on time history of the skin-friction coefficient for determining the transition onset and the transition length on the airfoil. The second is to apply transition γ-〖Re〗_θ model for laminar/turbulent transition simulation. For investigation of transition effect, the simulation repeated by use of a classical turbulent model and both results was compared with experimental data. The comparison shows that taking into account the transition effects gives a good agreement with experiment. Relative error of calculated drag coefficients for the transition based simulation is lower than 10%, while fully turbulent simulation are 70% overestimated in some incidences. Slipstream of upstream propeller changes flow pattern and boundary layer characteristics over the wing. Indeed in presence of propeller, spanwise load distribution and laminar/turbulent transition onset were affected. In propeller flowfield, increasing of velocity normal component over wing surface causes transition delay. Movement of transition onset to trailing edge on the upper surface in propeller downwash is representative of such phenomenon. On the other hand, in upwash region, the transition onset moves upstream. With the increasing propeller rotational speed, this tendency augments and so the transition onset on the wing upper surface moves far downstream in propeller downwash.

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Nowadays, the use of polymer-based composites has been growing. Composites due to mechanical, chemical and physical properties are widely used, but the inherent combustion of these materials and the lack of strength at high temperatures, especially when exposed to the fire is one of the challenges of using composites in industries. When composites are exposed to fire, matrix of composite decomposed with heat release, smoke, soot and toxic fumes. Due to the influence of fire on the composite structure, several thermal processes occur such as thermal conductivity in the structure, production and escape of the gases from the composite and resin decomposition. The aim of this study is the investigation of the effects of fire on the composite structures. Analysis of composite resistance to fire, determine the amount and duration of the fire-resistant composite as well as the effects of thermal stress in composite structure requires thermo-mechanical analysis of the composite. ABAQUS software is used for solving the problem in this study. Appropriate model for analyzing the thermal and mechanical parts of the problem according to the governing equations is developed and imported to the Abaqus software through Abaqus subroutines. Thermo-mechanical model validated with the results of valid studies. Finally, this model is used for thermo-mechanical analysis of a composite cylindrical structure exposed to the fire. The results showed that by estimating the failure time of the composite, it is possible to determine the amount of load that can be applied to the structure under different conditions of fire.