Computational study of performance characteristics for truncated conical aerospike nozzles

Aerospike nozzles are advanced rocket nozzles that can maintain its aerodynamic efficiency over a wide range of altitudes.It belongs to class of altitude compensating nozzles.A vehicle with an aerospike nozzle uses less fuel at low altitudes due to its altitude adaptability,where most missions have the greatest need for thrust.Aerospike nozzles are better suited to Single Stage to Orbit (SSTO) missions compared to conventional nozzles.In the current study,the flow through 20％ and 40％ aerospike nozzle is analyzed in detail using computational fluid dynamics technique.Steady state analysis with implicit formulation is carded out.Reynolds averaged Navier-Stokes equations are solved with the Spalart-Allmaras turbulence model.The results are compared with experimental results from previous work.The transition from open wake to closed wake happens in lower Nozzle Pressure Ratio for 20％ as compared to 40％ aerospike nozzle.