A scale Space Launch System (SLS) core stage engine single thruster was hot-fire tested at NASA Marshall for the SLS scale model acoustic test. This test program comprises a 5% scale model of the SLS vehicle and launch complex to determine liftoff acoustics and ignition overpressure environments. In addition, an updated liquid rocket engine turbopump dynamic transfer function, derived from the space shuttle main engine and J-2X oxygen inducer-im-peller pulsed waterflow test, has been incorporated into SLS core stage pogo stability models.
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