“…where thrust value S was obtained in N. From previously available data by one of the authors [5], the design point was set for a mass flow rate of m˙9 = m˙0 = 560 kg·s −1 at an altitude of 50,000 ft and at Mach 2.5. The parametric optimisation study was conducted using ANSYS Fluent in ANSYS Workbench 17, for the three nozzle types, and consisted of a data mining approach through a parametric analysis where a combination of multiple geometrical variables, i.e., length of the nozzle, curvature of the nozzle, and the height of the nozzle exit, were studied and the performance parameters compared to extract the best possible result for gross thrust production.…”