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Partially-averaged Navier-Stokes (PANS) method, as a bridging method between Reynolds-averaged Navier-Stokes (RANS) and direct numerical simulation (DNS), has attracted many researchers' attentions in recent years. In this paper, PANS is extended to the simulations of a jet injected into a supersonic crossflow. A dynamic function of the resolution control parameter f k (unresolved-to-total ratio of kinetic energy) is adopted. Numerical results are compared to the experimental data and the performance of PANS is evaluated. The predictions of dynamic f k PANS overall agree well with the measurements and the instantaneous flow filed is provided. In addition, the distribution of f k is presented to have a better understanding of the method's scale resolving behavior throughout the computation domain. Current study has shown the capabilities and potential of PANS method for supersonic industrial flows.