This work aims to study and simulate the behavior of flow over SAFAT-01's wing using numerical simulation based on solving Reynolds's Averaged Navier-Stokes equations coupled with K-ω turbulent model. The wing model is simple rectangular with elliptical ends. In the present work, aerodynamics characteristics and different flow phenomena were predicted at different design conditions (e.g. at different angles of attack) and at Re=5.2×10 6 . The present study analysis the vortices which occur over wing and captured their effective regions at critical design conditions. This study indicates that the maximum lift coefficient for SAFAT-01's wing is 1.44 occurred at stall angle of attack 12 o , maximum lift to drag ratio (L/D) is 26 which occurs at -4 o , and the zero lift drag coefficient is 0.0142. To validate this numerical simulation, a typical wing which found in Ref. [3] was analyzed, a comparison between predicted results and available results indicate that this numerical simulation has high ability for predicting the aerodynamics characteristics.

Erosion of compressor blades due to operation in dusty environments is a serious problem for the manufacturers and users of gas turbine engines, because of significant degradations in performance. This study has been devoted to estimating the change of performance parameters of an axial compressor stage due to erosive deterioration. The influence of erosion considered as consequences of a reduction of rotor blade airfoils, and an increase of tip clearance. The results of this study obtained using the CFD code “NUMECA Fine/Turbo”. This CFD code is a steady, quasi-three-dimensional Reynolds Averaged Navier-Stokes (RANS) solver. A Spalart-Allmaras turbulence model is used. The compressor stage parameters presented for three rotational speeds. Proposed a new approach to consider the changes of geometric parameters of blades due to erosion. Presented an analysis of the effect of erosion and its individual consequences on the pressure ratio, isentropic efficiency and stability margin of the stage. The obtained results verified using an existing experimental data.

This paper aims to represent a pelton wheel turbine that designed and fabricated in Omdurman Islamic University, faculty of engineering Sciences. The pelton wheel is designed using empirical formulae and its model is tested for the purpose to get its performance characteristics. The main geometric parameters which determined in this work are runner diameter, bucket size and nozzle diameter and dimension of other mechanical parts. The results which obtained by this design procedure are compared with that in available literature and they are acceptable.