As part of the composite compressor blade of aircraft engine concept study, a technical feasibility of replacing the current Titanium blades with fiber reinforced composite ones is evaluated here. This can result into substantial weight saving and may result in some cost saving too. In addition to the regular design criteria like stress and frequencies, survival under bird strike loading is also most important criteria. To evaluate composite blades made with different possible material systems under bird strike loading, is a time consuming and expensive task. In order to come up with a simplified method to evaluate the various possible cases, flat sub-element coupons are designed, fabricated and tested under bird strike loading in a real test facility. This simplified method is easy to use, fast and cost effective. This method generates strain allowable for different cases under bird strike loading using the combination of actual bird strike tests and the bird strike analysis of the same panel models in LS-Dyna software. This paper presents the results of the analysis and testing of these laminated composite panels and test analysis correlation. It is shown that strain allowable are easy to extract from the test-analysis correlation data.