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Papers by IJREI Journal
Lead-free soldering alloys with low melting point suitable for use in soldering joints are very e... more Lead-free soldering alloys with low melting point suitable for use in soldering joints are very essential. Use of lead as a solder is considered dangerous for the environment due to the huge number of printed circuit board and electronic devices, pipe joints etc. needed to be recycled from dumps. In this work the metallic samples were prepared from Bi in the mass range from 0.75gm. Samples of Sn were dropped into the bath of pure Bi by using an automatic dropping device. System required 40min time interval after every sample of dropped. Calorimetric measurements was done at temperature 830K. The Integral and partial enthalpy of mixing was calculated at this temperatures. The Integral enthalpy of mixing in Bi-Sn system at 830K is endothermic in nature throughout the composition and its maximum value at X sn = 0.6, is 1005.9061 respectively.
Alloy beams and beam like elements are principal constituents of many structures and widely used ... more Alloy beams and beam like elements are principal constituents of many structures and widely used in high speed machinery, aircraft and light weight structures. Crack is a damage that often occurs on members of structures and may cause serious failures of structures. In this research the natural frequency of a cracked cantilever beam is investigated by finite element method by using of ANSYS program with different crack depth and location effect. The beam material studied is aluminum alloy, titanium alloy, copper alloy and magnesium alloy. A comparison is made between these alloys and conclude optimized result between them. The increase of the beam length result in a decrease in the natural frequencies of the composite beam and also shows that an increase of the depth of cracks lead to a decrease in the value of natural frequencies.
Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was ... more Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was first studied by Strouhal. In this paper, the analysis of vortex shedding around a 2 dimensional circular cylinder with Reynolds No of 200, 500, and 1000 with different angle of attack 0 0 , 5 0 , and 10 0 has been studied. In this simulation an implicit pressure-based finite volume method and second order implicit scheme is used. Flow has been studied with the help of Navier-Stokes and continuity equations. The pressure, drag coefficients and vortex shedding for different Reynolds numbers and different angle of attack were computed and compared with other numerical result that show good agreement.
The displacement response of different masses of half car model. The analysis has been done for d... more The displacement response of different masses of half car model. The analysis has been done for different car models also to see the dynamic response of the driver body coupled with the seat of a vehicle. It has been assumed the driver body is rigidly coupled with seat of the vehicle. The vehicle has been modeled for two D.O.F, in two D.O.F Half car model two motion (Pitch and Bounce) have been considered. The response of the vehicle has been obtained for different velocities and different amplitudes sinusoidal bump excitation.
The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift fo... more The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, ratio of lift to drag etc. In this paper the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consist of steady state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performing at Reynolds number (1x10 6 , 2x10 6 , 3x10 6 , and 4x10 6) at different angle of attack (0 0 , 3 0 , 6 0 , and 9 0). The results give the satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtain in Re-4x10 6 at angle of attack 9 0 whereas low drag coefficient was obtain in Re-1x10 6 at AOA-0 0
The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift fo... more The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, ratio of lift to drag etc. In this paper the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consist of steady state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performing at Reynolds number (1x10 6 , 2x10 6 , 3x10 6 , and 4x10 6) at different angle of attack (0 0 , 3 0 , 6 0 , and 9 0). The results give the satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtain in Re-4x10 6 at angle of attack 9 0 whereas low drag coefficient was obtain in Re-1x10 6 at AOA-0 0
Lead-free soldering alloys with low melting point suitable for use in soldering joints are very e... more Lead-free soldering alloys with low melting point suitable for use in soldering joints are very essential. Use of lead as a solder is considered dangerous for the environment due to the huge number of printed circuit board and electronic devices, pipe joints etc. needed to be recycled from dumps. In this work the metallic samples were prepared from Bi in the mass range from 0.75gm. Samples of Sn were dropped into the bath of pure Bi by using an automatic dropping device. System required 40min time interval after every sample of dropped. Calorimetric measurements was done at temperature 830K. The Integral and partial enthalpy of mixing was calculated at this temperatures. The Integral enthalpy of mixing in Bi-Sn system at 830K is endothermic in nature throughout the composition and its maximum value at X sn = 0.6, is 1005.9061 respectively.
Alloy beams and beam like elements are principal constituents of many structures and widely used ... more Alloy beams and beam like elements are principal constituents of many structures and widely used in high speed machinery, aircraft and light weight structures. Crack is a damage that often occurs on members of structures and may cause serious failures of structures. In this research the natural frequency of a cracked cantilever beam is investigated by finite element method by using of ANSYS program with different crack depth and location effect. The beam material studied is aluminum alloy, titanium alloy, copper alloy and magnesium alloy. A comparison is made between these alloys and conclude optimized result between them. The increase of the beam length result in a decrease in the natural frequencies of the composite beam and also shows that an increase of the depth of cracks lead to a decrease in the value of natural frequencies.
Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was ... more Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was first studied by Strouhal. In this paper, the analysis of vortex shedding around a 2 dimensional circular cylinder with Reynolds No of 200, 500, and 1000 with different angle of attack 0 0 , 5 0 , and 10 0 has been studied. In this simulation an implicit pressure-based finite volume method and second order implicit scheme is used. Flow has been studied with the help of Navier-Stokes and continuity equations. The pressure, drag coefficients and vortex shedding for different Reynolds numbers and different angle of attack were computed and compared with other numerical result that show good agreement.
The displacement response of different masses of half car model. The analysis has been done for d... more The displacement response of different masses of half car model. The analysis has been done for different car models also to see the dynamic response of the driver body coupled with the seat of a vehicle. It has been assumed the driver body is rigidly coupled with seat of the vehicle. The vehicle has been modeled for two D.O.F, in two D.O.F Half car model two motion (Pitch and Bounce) have been considered. The response of the vehicle has been obtained for different velocities and different amplitudes sinusoidal bump excitation.
The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift fo... more The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, ratio of lift to drag etc. In this paper the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consist of steady state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performing at Reynolds number (1x10 6 , 2x10 6 , 3x10 6 , and 4x10 6) at different angle of attack (0 0 , 3 0 , 6 0 , and 9 0). The results give the satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtain in Re-4x10 6 at angle of attack 9 0 whereas low drag coefficient was obtain in Re-1x10 6 at AOA-0 0
The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift fo... more The performance of an aircraft wing mostly depend on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, ratio of lift to drag etc. In this paper the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consist of steady state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performing at Reynolds number (1x10 6 , 2x10 6 , 3x10 6 , and 4x10 6) at different angle of attack (0 0 , 3 0 , 6 0 , and 9 0). The results give the satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtain in Re-4x10 6 at angle of attack 9 0 whereas low drag coefficient was obtain in Re-1x10 6 at AOA-0 0