In the present investigation, Al2024-Beryl particulate composites were fabricated by stir casting by varying the weight percentage of beryl particulates from 0 wt% to 10 wt% in steps of 2 wt%. The cast Al2024 alloy and its composites have been subjected to solutionizing treatment at a temperature of 495°C for 2 hrs, followed by ice quenching. Microstructural studies were carried out to determine the nature of the structure. The Brinell hardness test was conducted on both the Al2024 alloy and its composites before and after solutionizing. Pin-on disc wear tests were conducted to examine the wear behavior of the Al2024 alloy and its composites. Sliding wear tests were conducted at various applied loads, sliding velocities and sliding distances. The results reveal that the wear rate of the composites is lower than that of the matrix alloy. The wear rate increased with an increasing applied load and sliding distance, and decreased with increasing sliding velocity.

A single cylinder diesel engine upgraded to operate Common Rail Direct Injection (CRDI) system and employed in this investigation. Tests were conducted on this engine using High-Speed diesel (HSD) and Simarouba biodiesel (SOME) blends to determine the influence of Injection Pressure (IP) and Injection Timing (IT) on the performance and emissions. Four unique IP of 400 bar to 1000 bar, in steps of 200 bar and four differing ITs of 10°, 13°, 15° and 18° before Top Dead Center (bTDC) combinations were attempted for the 25% to full load. Compression Ratio (CR) of 16.5 and Engine speed of 1500 RPM was kept constant during all trails. Critical performance parameter like Brake Thermal Efficiency (BTE) and Brake Specific Fuel Consumption (BSFC) were analyzed, primary emission parameters of the diesel engine The NOx and Smoke opacity were recorded. Finally, the outcomes of each combination were discussed.

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Since the beginning of civil aviation, icing has been a severe weather hazard for aircraft operation. For many years, the term engine icing has been used to describe ice accreting on exposed engine surfaces as an aircraft flies through a cloud of super-cooled liquid droplets. The concern arising out of aircraft icing is due to its adverse effect on flight safety and hence, for decades, a considerable amount of research is on in the area of icing of aircraft and its components exposed to ice. Experimental verification and some of the key numerical investigations in the area have revealed that aerodynamic characteristics and controllability of an aircraft are affected by the amount and type of ice accretion at different locations. Fundamentally icing of airfoil of an aircraft contributes to decrease in lift force as well as the angle of stall on the wing. This also brings up another situation that is longitudinal instability of the apparatus concerned. It has been a complex physical situation to comprehend the accretion process and its impact. In the present study NACA0012 airfoil geometry has been used to understand the accumulation and accretion process through simulation. The results of total mass of ice accreted with respect to total time of accretion (tice) have been presented