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In this research the transient flow analysis in viscoelastic pipes considering Fluid Structure Interaction have been performed utilizing a newly developed formulation of Transfer Matrix Method in frequency domain. To obtain this extended form of TMM, mathematical processes was accomplished. Time domain governing equations have been transformed to frequency domain and then a suitable matrix form of them is used to study transient flow due to sudden valve closure. Obtaining a set of algebraic equations instead of integral equations and the ability to analyze this phenomenon without need to solve complex convolution integral, are some of the benefits of the frequency domain tools, which have been applied in this research. To verify the model, initially two cases of rigid and elastic pipe wall have been analyzed. Results showed good conformity comparing to experimental data and analytical solution available. Then having a set of reliable experimental data of transient flow in VE pipe, MatLab code was adopted to the model and fortunately here also results were in good compatibility with the experimental results. Also it has been showed that this model will be a suitable tool for parametric analysis and for determining the critical situations of the system. The results obtained from this research prove that using frequency domain tools will lead to an effective and precise model for simulating the transient flow characteristics in VE and also normal transmitting pipelines.

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In this paper, the importance of accurate estimation of the aerodynamic performance of delta wing has been mentioned. Some available and conventional methods of estimating the aerodynamic coefficients composed of CFD methods and industrial and commercial software have been selected and for comparison, a wing similar to delta wing mounted on Pegasus Air-launch-to-orbit missile as a template is being selected. The reason for this selection, mainly is the lack of wind tunnel in design process and flying in a wide range of flow regimes. As many parameters may be utilized in design process such as the aerodynamic force and moment coefficients, stability derivatives, heat transfer coefficient and the structural loading parameters are being required. In this study, the accuracy of the results of different methods in estimating the force and moment coefficients, as the most significant quantities for performance analysis, at any flow regime has been checked and the suitable method has been introduced in terms of the flight condition. With respect to available parallel processing system, different CFD methods are compared together. Then validity of solution of Reynolds-averaged equations (RANS) and Euler method have been evaluated based on the comparison by DES solutions. Therefore, the valid intervals of the subsequent methods have been presented. Results are indicating the advantage of computational methods to industrial and semi-empirical software. Semi-empirical code and industrial software are shown satisfactory for computation in the linear range i.e. the small angle of attacks.

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In this paper, the Semi-Empirical and numerical methods that can be used to investigate the effects of dynamic stall are compared with each other, and the capabilities of the methods are studied. The experimental measurements have been used in order to compare the methods. The Semi-Empirical Leishman-Beddoes (L-B), Snel and ONERA methods have been used, and the finite volume method was being used for numerical simulations. The lift coefficient was being calculated by all the methods at various conditions, and the drag coefficient had been computed by the numerical and Leishman-Beddoes methods. The parameters that have been used in order to compare the methods, are the maximum lift coefficient value, the angle of attack of the largest lift coefficient, the error at upstroke phase and the error at down stroke phase. The results show among the semi-empirical models; the L-B method has the highest precision to predict the lift coefficient, and although the numerical method can investigate the flow with more details, but the error percentage at the down stroke phase is higher than expectations. The results from the drag coefficient modeling show that the numerical method can predict this coefficient better than the L-B method. The results also can help other researchers to select the best dynamic stall model in order to investigate the wind-turbine aerodynamics.