The use of laminated fiber reinforced composite structures is limited by the delamination type of failure under various types of loading. Early researchers did some attempts to come out with a methodology for modeling delamination behavior under static and dynamic impact loading. These early attempts were mostly talking about the unidirectional laminates due to difficulties in modeling the multi-directional laminates for delamination behavior. The real world, however, use the multi-directional laminates only due to their distinct advantages. This article is a sincere attempt to develop a mode I delamination prediction process for multidirectional carbon fiber composite laminates (with various interfaces like 0-0, 45-45 and 90-90) under quasi-static and dynamic impact loading. For modeling the behavior under quasi-static loading, ANSYS software is used with its in-built contact definitions based cohesive zone model. The mode one type failure tests were conducted on multidirectional carbon fiber composite coupons as per available standards and their load displacement behavior is validated using the FEA cohesive zone models. The mode I test coupons are modeled as per the real specimens and the delamination failure is studied/validated in the simulation. For dynamic impact type loading, LS-DYNA software is used with its the inbuilt tiebreak type contact option capabilities which are almost similar to that of cohesive zone elements. The conclusions show that cohesive zone models can match the delamination behavior in this kind of composite materials under static and dynamic impact type loading. The modeling methodology/process needs to be further improved through application and validation with different geometries and loading rates for both situations to make it more robust and ready for applications to aerospace composites.