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This paper aims in assessing the effect of biofuel blend such as butanol, jatropha methyl ester, soya methyl ester and rapeseed methyl ester as an additive for the aviation fuel. In addition to the blends, the nanoparticle TiO of 3 % is added to the biofuel. The nanoparticle mixed at the concentration of 300ppm by ultrasonication process. The fuel Jet A, B27T, J27T, S27T and R27T are investigated for combustion and emission characteristics for various throttle settings in micro gas turbine engine. Addition of additives improves the ultimate property of the fuel by reducing the kinematic viscosity. The fuel blend B27T reports 25 % increase in total static thrust and 22 % reduction in thrust specific fuel consumption. From the results it is evident that, all fuel blends showed a significant reduction in emission values owing to high oxygen content. In addition, the thermal efficiency of the B27T and J27T is improved appreciably to 30 % and 10 % higher than Jet A fuel owing to the influence of the nanoparticle TiO . On the other hand, the emissions like CO and NOx reduced drastically up to 70 % and 45 % respectively.

High-lift systems are designed to expand the flight envelope and have a most important effect on the size of the wing, economy, and safety of many airliner configurations. Even a small increment of lift using a high-lift system can significantly impact an aircraft’s profitability. The effective design of the airfoil shape with the required aerodynamic performance is still difficult. In the early days, the designs of airfoils were randomly set up and tested in the flow section, and then, the Wright brothers emerged with a cambered section. NACA has provided an appropriate airfoil definition that supports us in making airfoil designs using formulas, not randomly. This paper describes the influence of aerodynamic analysis of wing with flaps at various deflection angles. Aerodynamic variables for the aircraft wing, which is made up of the NACA airfoil 6412 model with and without flaps, have been studied at various angle of attack (AOA) (i.e., -4, -2, 0, 2, 4, 6, 8, 10, 12, and 16) and different Mach number at 0.2, 0.3, and 0.4. Also, the analysis was done for the 15000 ft altitude to check the density effects for the real-time applications. The coefficients of lift and drag are gained by examining the pressure distribution over the surface of the wing. Lift increases as the approach ascends from a low to a high angle of attack, and the most extreme lift is produced at a specific point. After that, when the angle of attack increases further, the drag component increases, so the stall occurs at that point in time. The results showed that the NACA 6412 airfoil obtained the maximum lift at 14°, and the lift value started to decrease. The CFD computations are performed in Ansys Fluent by performing hybrid mesh using ICEM-CFD. The analysis is performed for various configurations of the wing section, and the effects of flow parameters like angle of attack, altitude, and the gap distance between the main wing and slotted flap were compared to identify the better configurations.

The Aircraft wing is a point of important research which poses greater challenge in terms of aerodynamic efficiency. The flow separation control method is addressed in classical aerodynamics methods. This study focuses on influence of dimples on controlling the flow and also increasing the aerodynamic efficiency. The periodic process of placing the cavities on the wing starting from root to tip controls the flow separation. The linear variation of characteristic curve provides the information about the flow separation and control of flow on upper surface of the airfoil.These different shapes are utilized viz., Square, Rectangle and Triangle. The numerical simulation is carried out in using MATLAB package. Preliminary analysis on the flow separation is carried out focuses on laminar flow separation, which has the influence on the overall lift generation and drag generation.

The use of dimpled surface for enhancement of lift is getting popular at recent days. In our previous research [16] we have studied the aerodynamic behaviour of dimpled surface numerically. In this work enhancement of lift without increase in drag on dimpled NACA0012 airfoil were studied experimentally. Dimples of various geometrical structures like square, rectangle and triangular were taken for consideration and underwent computational analysis by developing 3D model using CATIA V5. Flow analysis was done using ANSYS CFX. Based on the computational results, square dimple was chosen as the best and considered for the experimental work. It was found that the deviation between the computational simulation and experimental results were within 0.5%.

The quantitative effects of cutting speed, feed and depth of cut on surface quality of the turned 316 LVM stainless steel work piece and tool wear of the TiAlN/CrN coated insert was investigated using Response surface methodology. Subsequently, FEM analysis of the tool wear using DEFORM-3D software was carried out. ANOVA analysis was formulated and regression was performed to understand the interactive effect of the process variables on the quality indicators. Further, a FEM-based method is defined to predict the advancement of tool wear during cutting operations. The cutting process was simulated using Deform 3D FEM software, and a suitable subroutine was added to the software to assess tool wear. An estimation of the tool wear value is made using well-known analytical models. The FEM model was calibrated and validated through experimental tests by turning 316 LVM stainless steel with ISO P40 TiAlN/CrN coated tools. The results from the FEM analysis and the experimental data were in good agreement.