02-02-2016, 10:26 PM
Abstract: The analysis of a rocket nozzle involves the concept of "steady, one-dimensional compressible fluid flow of an ideal gas". The goal of rocket nozzle design is to accelerate the combustion products to as high an exit velocity as possible. This is achieved by designing the necessary nozzle geometric profile with the condition that isentropic flow is to be aimed for. Isentropic flow is considered to be flow that is dependant only upon cross-sectional area -- which necessitates frictionless and adiabatic (no heat loss) flow. Therefore, in the actual nozzle, it is necessary to minimize frictional effects, flow disturbances and conditions that can lead to shock losses. In addition, heat transfer losses are to be minimized. In this way, the properties of the flow are near isentropic, and are simply affected only by the changing cross-sectional area as the fluid moves through the nozzle.
Space shuttle uses some of the largest De-Laval nozzles in the Solid Rocket Boosters(SRBs). They are designed so as to optimize the weight and the performance. In this project a study is conducted to study the various configurations and geometries of a De-laval nozzle w.r.t the available technologies been used in the world. Further an effort is made to analyse the flow of gases through a Space shuttle nozzle using commercially available software.