Computational Exploration of Flow Field Within An Aerospike Nozzle

Abstract

To improve the single stage rocket's current performance, new rocket designs are being used. However, the concept of the aerospike nozzle, which has been developed since the 1950s, has not been applied to a launch platform. The aerospike nozzle is more efficient than other nozzle types because of its geometry, which allows it to change its outer jet boundary in response to changes in its surroundings. The nozzle contour's coordinates are obtained using MATLAB and a straightforward approximation technique. The flow behaviour of an aerospike nozzle was analysed in Ansys software by applying various boundary conditions. The nozzle was designed in CATIA V5 with some assumptions. Additionally, these designs were simulated for various pressure outlet conditions in order to assess the effectiveness of the full-length spike at various altitudes. The outcomes were then compared between the Bell nozzle and the currently in use aerospike nozzle