Examining the Mach number in different sizes of the throat radius for different sizes of divergent part angles in convergentdivergent nozzles

Analyzing the problems of shock wave interference in supersonic flowsin rockets and airplanes, as well as inside nozzles, is very important. Itsapplications are used in the aerospace industry and material science. Inthis study, the simulation has been conducted by solving the axiallysymmetric flow, and the conditions governing the flow in theconverging and diverging nozzle have been considered as single-phaseand two-dimensional. In this research, the Mach number in aconverging and diverging nozzle with a fixed converging angle degreeat different angles in the diverging part has been investigated in threecases: throat radius of ۵, ۷, and ۱۰ mm. Additionally, for each throatradius, four different diverging angles (۲۱, ۲۷, ۳۳, and ۳۹ degrees) havebeen examined. This study has shown that, in general, the Mach numberincreases in all three throat radii with increasing divergence angle.From the graphs depicting the Mach number, it is evident that the radiusof curvature ۷ and angle ۳۹ is greater than the radius of curvature ۵ and۱۰ with other angles.

Keywords:

throat radius , convergent-divergent nozzle