Theoretical and Computational Investigation on Aerospike Nozzle Equipped with Exhaust Plumes for Supersonic Flow Regimes

Aerospike nozzles are widely used in aerospace applications due to their high performance, low cost, and low maintenance. They have been widely used to improve the performance of aerospike engines. This paper presents a computational and numerical analysis of the flow behavior of aerospike nozzles equipped with exhaust plumes under different operating conditions, contributing to the better study and understanding of fluid dynamics for the aerospike nozzles in the field of aerospace engineering. The study uses a three-dimensional, axisymmetric model to simulate the flow within the nozzle and the results are later used in order to generate better contours and performance. An iterative test has been carried out which in turn is used for an optimization loop which involves changes in contour shape, spike height, or spike angle to achieve better flow expansion and reduce pressure losses. The paper also discusses the potential future research directions, such as investigating unsteady flow phenomena or exploring advanced turbulence models for more accurate predictions.