Performance analysis of aerospike rocket engines

摘要

The results of an experimental and analytical investigation of the characteristics of the separated flow region for an aerospike nozzle are presented. The primary objective of the investigation was to predict base pressure in the flow recirculation area for open- and closed-wake operation to determine overall engine performance. The developed analytical method and the results of parametric studies including the effects of sonic line shape, internal shock, ambient pressure, base bleed, nozzle area ratio, turbulence effects, plug length, and aerodynamic slipstream are described. A high area ratio, truncated aerospike nozzle as considered by Chrysler Corporation in their single-stage, earth-orbital, reusable vehicle study is discussed, and the performance for various operating conditions is presented.