The impact resistance and impact damage tolerance of an aerospace grade high performance 5 Harness Satin woven fabric carbon fiber reinforced/polyphenylene sulfide matrix (CF/PPS) thermoplastic composite were investigated experimentally and numerically. The numerical modeling was performed using the experimentally determined parameters of material model MAT-58 and Hashin failure criteria in LSDYNA using the single shell and stacked shell models. The numerical models of the low velocity impact (LVI) tests showed good correlations with the experimental tests while the stacked shell model showed nearer results with the experimental tests. The stacked shell model also estimated the LVI test delamination areas, which were comparable with the experimental damage areas. The LVI tested coupons were further subjected to compression after impact (CAI) tests to determine the damage tolerance of CF/PPS composite. The CAI tests were modeled using the single shell model. The numerical models of the CAI tests showed very similar trends with the experimental CAI tests. The trends were shown to be more converging in the specimens tested at 3 m/s and above in the LVI tests. Lastly, three high velocity impact (HVI) tests were performed at around 100 m/s. The failure mode of the HVI tests was shown to be very different from that of the LVI tests. The long longitudinal and transverse cracks were formed in the HVI tests. The delamination damage in the HVI tests determined using the stacked shell model was found to be more comparable with the experimental delamination damage determined by the C-Scan.