Abstract
The propulsive performance was estimated for the H2/Air PDE with an aerospike exhaust nozzle using multi-cycle two-dimensional limit cycle simulations with the detailed chemical reaction model. The present simulation also compared with the results for a convergingdiverging nozzle. The present results show that Ispf and F for the aerospike nozzle is 14% and 15% lower than those for the CD nozzle at M=2.1 and H=9.3 km. Most of the thrust for the CD nozzle is produced by the momentum thrust, however, the pressure thrust for the aerospike nozzle is approximately 30-50% of the momentum thrust.
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