Physics Project Abstract
EFFICIENCY STUDY OF ROCKET NOZZLE SHAPES
Presenter:
Stephanie Pasquesi, Illinois Mathematics and Science Academy, 1500 West Sullivan Road, Aurora, IL, 60506; stephp@imsa.edu
Advisor:
Mr. Ray Urbanski, Illinois Mathematics and Science Academy, 1500 West Sullivan Road, Grainger Inventors Workshop, Aurora, IL, 60506; 630-907-5959; rurbanski@imsa.edu
Abstract:
The purpose of this study has been to determine the relationship between the amount of thrust produced by a rocket engine as affected by the shape of the exhaust nozzle. The nozzle is the component of a rocket engine that generates thrust by converting thermal energy from hot chamber gases into kinetic energy and directing that energy along the nozzle's axis. The main purpose of the nozzle is to expand the gases as efficiently as possible to maximize the exit velocity. The most important factor in rocket nozzle design is therefore, the expansion area ratio, that is, the ratio of the exit area to the throat area. I have focused on two popular nozzle shapes, parabolic (bell) and conical. The difference between these two shapes is the divergence angle. Through the use of a force transducer and computer software, I plan to obtain thrust data to analyze the efficiency of each nozzle shape. Preliminary testing at 10 psi propane has shown that the thrust from the parabolic nozzle is so great that a sustainable amount of pressure is exceeded and safety measures were activated. Further testing is underway at lesser propane pressure and a lesser ratio of oxygen gas to propane.