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With the intend to study the flow behavior over cruise missiles and rockets, we aim to perform numerical simulations over circular cross-section models in supersonic flow regime specifically Mach 2 at different angles of attack. These simulations and investigations would provide us with axial and normal forces and moment coefficients which would further be used for obtaining aerodynamic forces. The models are to be created in CATIA v5 and then exported to ANSYS Fluent for analysis and calculations. With accordance to iterations and numerical solutions these models will be verified and validated with special considerations on formation of shockwaves. In conclusion, the computational fluid dynamics (CFD) results will be compared and analyzed with the experimental data. In future, the project has the scope to develop additional structures like fins or other control surfaces on the configurations to improve the performance and further compare them with each other. It could further lead to a step-by-step process of designing a complete aerodynamically efficient rocket or missile depending upon the prosperity requirement. [ABSTRACT FROM AUTHOR]

Even though symmetrical airfoil has less lift-drag ratio and the undesirable stall characteristics it has been used in the rotary wing applications. Increasing the aerodynamics efficiency by using the different flow control methods are the important research in recent years. Amplifying the lift coefficient without causing any negative impact on the drag coefficient will create the great impact on aeronautical domain. Hence this paper objective is by using cylinder rotation- an active flow control method to improve the aerodynamic efficiency over the airfoil. To get the optimum values of lift and drag coefficient the flow parameters, velocity ratios of the cylinder Vc / V∞ and the location of the cylinder have been used. The model of the NACA 0012 airfoil with cylinder is developed by using Inventor and the numerical analysis were carried out by using Ansys fluent. Analysis was carried out for the velocity ratios of 0.5,1 and 2 by placing the cylinder at the chordwise locations of 10% to 50% of its length. When compared the results of NACA 0012 airfoil with cylinder and without cylinder there is a significant growth in aerodynamic efficiency and delayed in stall angle. Generally, the performance was increase in the ratio of cylinder rotation speed Vc to the freestream speed V∞. There appears to be an optimal location for the rotating cylinder which gave quite promising results. [ABSTRACT FROM AUTHOR]

Interpretive Structural Modelling (ISM) is applied for interpolating the factors dictating the implementation of lean and sustainability concepts in aerospace sector. Modern aerospace component manufacturers are expected to be lean and sustainable to sustain in the competitive market scenario. Lean and sustainable strategies offers benefits such as waste elimination and minimal environmental impact. ISM has been preferred to create the structural model to explore the interrelationship between factors. 15 major factors are identified from prior art and further validated based on expert opinion. Based on computation, the influential factors are being identified and the structural model developed, management infrastructure and customer pressure factors are found to have top priority. The study has been conducted with inputs from expert and practitioners and the study is focused on aerospace sector. Hence, the outcomes are practically valid based on case study. [ABSTRACT FROM AUTHOR]

The shock wave exposure-based studies have been widely focused on the recent years. A material irrespective of its strong mechanical property depending upon the threshold capacity and withstanding pressure of shock wave, the variation in structural changes occur. NiW based thin films are deposited by DC electroplating process in a citrate-based bath solution with two different varying temperature conditions. The deposited thin films are exposed to shock wave using the shock tube. The shock wave exposure conditions were varying of pressure in bar. The shock wave exposed thin film are characterized for FESEM and the analysis shows a trend of agglomeration for shock wave exposed thin film than the unexposed NiW thin film. According to the deposition conditions taken into consideration the higher temperature deposition showed nanostructured agglomeration. This study therefore depicts morphology of sample has been enhanced and its dependence on shock wave exposure, deposition process condition. [ABSTRACT FROM AUTHOR]

Natural fiber- reinforced composites are currently being researched for their selection and use in the industries spanning aerospace, automotive, ground transportation, and several other high- performance-critical end products. Two of the key reasons in favor for the selection and use of natural fibers are, their biodegradability coupled with an overall ease of availability that makes the production of engineered composites not only cost effective but also economically viable. However, the selection and use of natural fibers/matrix is curtailed primarily because of three competing drawbacks, namely (i) high moisture absorption, (ii) inferior mechanical properties, and (iii) poor interfacial bonding strength between fiber and matrix, when compared one-on-one with the synthetic fibers/matrix. Due to these reasons, natural fibers are often used in combination with synthetic fibers for engineering composites, so as to achieve a material that offers the possibility of improved performance at the desired level. In this research study, composite laminates with novolac resin and sisal/coir/E-glass fiber reinforcement (60:40) were fabricated using the hand lay-up method. The fabricated composite laminates were characterized for macromechanical properties, namely, tensile strength and water absorption test was conducted to explore the moisture absorption characteristics of composite laminates. Test results revealed the composite laminates with natural fibers/resins to possess many attributes in favor of their selection and use in structural components. [ABSTRACT FROM AUTHOR]