Computational analysis of thruster nozzle / Syed Daniel Shukri Syed Mohd Tahir

Aviation and Space travel has become more important, demand need to be met with better technology via in depth research on the matter, thruster is propulsive device used by aircraft and spacecraft for altitude control. Thrust force is generated by combustion of propellant which is the fuel and oxidizer within the thrust chamber, that turn the combustion effect to thrust force that accelerated and ejected at high velocity through a nozzle thereby imparting momentum to the system. There are several distinctive variables that determined the efficiency of the thruster nozzle, one of the most important and effective method to do so is by possessing the most superior nozzle configuration. Research is done to studies the effect of variable changes in nozzle design to thruster nozzle parameter, they are subjected to the same flow condition while applying constrain of flight simulation on a sea level altitude. Six different geometry of nozzle divergence section which varies in angle and length, would be studied based on the criteria set under the studies constraint. These studies could aid us by ensuring better understanding of flow characteristic in nozzle studies with emphasize on nozzle configuration by providing comprehensive research information and visualization interpretation via simulation. Also, it is with great expectation that the nation would be interested in further aviation studies where this research could be the basic guideline of thruster design.