The multi-fluid framework Hall2De is updated to perform simulations of Hall thrusters operating with krypton propellant. A series of eight simulations of the NASA-300M thruster are performed with both xenon and krypton and the implementation is validated by comparison to experimental measurements from NASA Glenn Research Center. For all operating points the computed thrust matches experimental values to within 10%. Krypton gas generates a specific impulse value between 10 and 16 percent higher than xenon propellant, while producing thrust values between 15 and 25 percent lower than in the xenon simulations. These results are consistent with a back-of-the-envelope theoretical calculation. Next, an unshielded H6 thruster, which has not yet been operated experimentally with a krypton propellant, is also simulated. A 28% lower mass flow rate of krypton gas is required to operate the thruster at the same 6 kW power level as with xenon propellant. The performance trends observed are consistent with the NASA-300M thruster simulations. Further, the singly charged ion current fraction for xenon is lower than for krypton, while for the higher charge species the trend is reversed. This behavior is explained by the relative differences in cross-sections between the different ionization processes for the same gas.
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