Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Abstract

The scope of this work was to perform a new three-dimensional MLN shape design of supersonic nozzles with an arbitrary exit cross section. The shape design is done by making a transition from the axisymmetrical nozzle using the streamline definition in space. The study is made at high temperature, however, less than the dissociation temperature. Studying asymmetric nozzles is very important for the improvement in the axisymmetric nozzles efficiency, higher Mach number, mass and thrust coefficient. Three cases are considered in order to find a three-dimensional nozzle shape with equal mass, the same exit Mach number and the same throat area compared with the axisymmetric geometry. The difference between the perfect gas model and our high-temperature model is presented. Calculation can be performed for any selected 3D nozzle exit cross section. Hence, an infinite number of nozzle shapes are available, depending on the selected exit Mach number, stagnation temperature or exit cross-sectional shape. The application is for air.