主催: 一般社団法人 日本機械学会
会議名: 2021年度 年次大会
開催日: 2021/09/05 - 2021/09/08
In this experiment, the aerospike engine combustion gas was visualized using the Schlieren method. Propellant were hydrogen and oxygen gas. Though the combustion gas choked at the throat, the shock wave was not observed around the nozzle.The characteristic exhaust velocity was evaluated, using the estimated propellant flow rates. C*efficiency was evaluated to be 0.997, using the calculation result by NASA CEA.