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The elastostatic responses of a symmetric cross-ply and angle-ply laminated composite panels are analyzed in a comparative fashion using a single-variable lamination theory. A finite-difference computational scheme is developed for the application of the present theory to practical problems of composite mechanics. Deformed shapes as well as critical ply-stresses of the laminated panels are discussed for both the cases of flexural and axial loadings. A comparative analysis is also included to verify the soundness and accuracy of the present computational approach.

Every compressor has a stall line. In the vicinity of the stall line, the flow field is inherently unsteady due to the interactions between adjacent rows of blades, formation of small stall cells, flow separation and the viscous effects including shock-boundary layer interactions. These factors may aggravate to a state of local breakdown of flow or a total breakdown of flow or with a disastrous flow reversal. This paper starts with an overview on the previous researches about compressor stall and surge. Subsequently, it describes the effects of these instabilities in overall engine performance and design with/ without any control. The main objectives of this paper are to review the phenomenon of instability and methodology to suppress the rotating stall and surge by enlarging the stable operating range of compressor with the application of various control systems. This paper surveys research developments in this field and also tries to find an improved solution to increase the engine performance by applying various surge control strategies. Finally, the paper focuses on some recommendations towards a better design of compressor especially for aircraft power plant.