Mohamad Nor Musa

Thermal Conductivity for Mixture of Rice Husk Fiber and Gypsum

This project is conducted with aim to determine the thermal conductivity for mixture of rice husk fiber and gypsum. The thermal conductivity value for 100% gypsum is also determined in this project for comparison purpose. The experiment used the Guarded Hot Plate Method, single specimen apparatus. This method is based on one-dimensional heat flow through conduction and steady state technique. Four samples have been tested which are 100% gypsum with a mass of 1kg for sample 1, a mixture of 0.1kg of rice husk fiber and 1kg gypsum for sample 2, mixture of 0.2kg of rice husk fiber and 1kg gypsum for sample 3 and a mixture of 0.3kg of rice husk fiber and 1kg gypsum for sample 4. From the data of the experiment that have been carried out, the value of thermal conductivity is decreasing with the increasing of rice husk fiber in the sample. The value of thermal conductivity is 0.772W/mK for sample 1, 0.7574 W/mK for sample 2, 0.7469W/mK for sample 3 and 0.7368W/mK for sample 4. The rice husk fiber is a bio-waste material and the mixture of rice husk fiber and gypsum will add value to the material as gypsum are widely used in construction field such as for plaster ingredient and ceiling finishing because it is a good insulator. The mixture of rice husk fiber and gypsum improve the 100% gypsum thermal conductivity and therefore the mixing of these two materials should have bright application potential.

Analysis of Center Pivot Irrigation System by Experimental Method

The objective of this project is to design a center pivot irrigation system and determine the efficiency of the system by using experimental method by build a model of the system. For that, a literature study is carried out to understand the theories of center pivot irrigation system. Center pivot irrigation system is the system that can rotate 360 degree around the center pivot. Before model build, the theoretical calculation need to be done to calculate the specification of the model. The model of the experiment purpose build not included the rotation part because the rotation part not gives an effect to the water flow. The experiment procedure follows the standard of North Carolina State University that conducts this type of experiment. From the experiment, the uniformly efficiency of the irrigation system can be defined. Scaled model use in this experiment to determine the uniformly efficiency by using specification from the theoretical calculation. From the previous experiment the uniformly efficiency of the irrigation system is 50% - 60% and the uniformly efficiency of center pivot irrigation system is about 75% - 90%.

Effectiveness of Jet Impingement Cooling System on Convex Surface

Jet impingement is one of cooling method used in order to achieve high heat transfer coefficient and widely used in industry applications such as drying of textile and film, glass and plastic sheets, cooling of electronic equipment, and heat treatment of metals. In this research, it focused on the effectiveness of the jet impingement cooling system on the convex surface based on mass blowing rate and nozzle exit to surface parameters. The scope of experiment research encompasses are convex surface made of aluminum alloy and diameter 12.5cm. For mass blowing rate parameters, it use ʋjet = 1.98m/s, 3.03m/s, 4.97m/s and 6.00m/s which has Reynolds number range from 643 until 1946. Nozzle exit to surface distance,s/d = 4.0, 8.0 and 12.0. In this experiment model, a major components that involved are a compressor, nozzle, convex surface model, K thermocouple and heater. For the result of the experiment, it is based on the data obtain through a heat transfer coefficient and Nusselt number which the plotted graph focus on the space spacing and Reynolds number parameters. For the graph Nusselt number versus s/d at stagnation point c/d=0, it shown that when the Reynolds number increase, the Nusselt number also increase. In term of effectiveness, the s/d=12.0 has a good effectiveness jet impingement cooling system. For the graph of Nusselt number versus Reynolds at stagnation point, c/d=0, as Reynolds number increase, the Nusselt number increase too. From this experiment the better cooling effect is at Reynolds number, Re=1946. Thus, it can conclude that, effectiveness for jet impingement cooling system on the convex surface occurs at the highest Reynolds number.

Aerodynamic Analysis on Proton Preve by Experimental

The purpose of this study is to determine the coefficient drag, CD of the Proton PREVẾ by experimental method using Low Speed Wind Tunnel. All the relevant data are collected through the literature reviews from books and journals. First, the basic thing in aerodynamic is studied. There are two things are concern when studies aerodynamics. They were air flow and vehicle shape which we regard as aerodynamics factor that determine aerodynamic of the vehicle. Fundamental of air flow and vehicle shape is reviewed includes the relationship between air speed with pressure, boundary layer, Reynolds number, drag, lift drag and shape optimization. Wind tunnel is also studied before the experiment. Five selected speed were been tasted during the experiment to determine the CD value.

Jet Impingement Cooling System on the Pressure Side of Turbine Blade

This study is to investigate the effectiveness of jet impingement cooling system on the turbine blade pressure side. The objective of this study is to determine the mass blowing rate referred to Reynolds number and the nozzle exit to surface distance which will produce the highest cooling effectiveness which will be shown as Nusselt number. A model of CF6-50 blade is made from mild steel and an experiment to study the jet impingement cooling effectiveness on the pressure side of turbine blade is conducted. The parameters that are included in the experiment are the Reynolds number, Re = 646, 1322, 1970 and 2637; and nozzle exit to surface distance, s/d = 4.0 cm, 8.0 cm and 12.0 cm. The results obtained are calculated and graphs for each experiment are made. The result shows that the jet impingement cooling effectiveness are the highest at where the nozzle is pointed and the cooling effectiveness decreases as it travels further away on the blade. The theory of jet impingement cooling is presented and the several factors that affect jet impingement cooling are also discussed.

Air Flow Analysis in Square Duct Bend

This paper present new result for experimental analysis of air flow velocity and pressure distributions between two ducts bend: (1) 90° duct bend with a single turning vane having 0.03m radius and (2) 90° duct bend with double turning vane, in 0.06 × 0.06 m duct cross section. The experiment used five different Reynolds numbers chosen between the ranges 1 ×104 and 6×104. Each experiment has four point measurements: (1) point 1 and point 2 at cross section A-A and (2) point 3 and point 4 at cross section B-B. The first experimental study used single turning vane radius 0.03m with inlet air velocity from 2.5m/s to 12.2m/s. And for the second experiment that used square turning vane with 0.03m radius. In experiment 2, the inlet air velocity also start from 2.5m/s to 12.2m/s. From analysis results, the pressure drop in experiment 1 is higher than experiment 2. As example the maximum pressure drop at 7.5m/s inlet air velocity between point 1 and 3 was found to be 71.6203 Pa in experiment 1 as compared to 61.8093 Pa in experiment 2. The velocity after duct bend is greater when using double turning vane compare used single turning vane as maximum velocity at point 3 in experiment 2 compare to velocity at point 3 in experiment 1 that is 55.677× 10-4 m/s and 54.221× 10-4 m/s. The velocity at duct wall is equal to zero. When increase the value of Reynolds number or inlet velocity, the maximum velocity and total pressure also increase. For example in experiment 1 at point 1, the velocity is 48.785 × 10-4 m/s at Reynolds number 1 ×104 and velocity 65.115×10-4 m/s at Reynolds number 12.2 ×104 . Velocity flow in duct section are lower than inlet velocity. In experiment 1, the inlet velocity is 2.5m/s meanwhile the maximum velocity in the duct section at point 2 is 73.075×10-4 m/s that is much more lower than inlet velocity.

Aerodynamic Analysis on Proton Inspira by Simulation

The purpose of this project is to study the airflow from across Proton Inspira car and evaluate the drag force and drag coefficient of the Proton Inspira car by simulation. All relevant data are collected through the literature review from book and journal. In methodology, model specification and simulation procedure is explained, together with consider assumption. Five selected speed were been input to the software to determine the CD Value. The calculation and graphical result has been generated by the software and discussed.