Design of smooth supersonic nozzle profile using method of characteristics.

Basically, two categories of supersonic nozzles exist: conical contour nozzle (CCN) and thrust-optimized contour nozzle (TOCN). Conical nozzles are easier to design/manufacture, with little complexity whereas TOCN (bell-shaped nozzles) require more attention. However, the TOCN design allows for better expansion of exhaust gases even over shorter lengths. The present work explains method for designing the contour of a supersonic thrust-optimized nozzle using the method of characteristics (MOC). The design is based on the exit Mach number and specific heat ratio. Furthermore, this study deals specifically with the divergent section of the nozzle by implementing assumptions and/or calculations to the throat. The exit Mach numbers of 2.0, 2.5, 3.0, 3.5, and 4.0 with 100 characteristic lines are computed using method of characteristics and MATLAB. The expansion area ratio is compared with the ideal value and the respective error percentage is calculated for the given exit Mach numbers. [ABSTRACT FROM AUTHOR]