Meso-scale numerical simulations of composite coupons typically employ a ply-by-ply discretization approach, requiring numerous material properties to characterize the anisotropic elastic and failure behaviour of each ply. This study leverages the observed interrelations among the elastic and intralaminar (ply-level) properties of various carbon-epoxy systems to develop a streamlined procedure for rapidly estimating meso-scale parameters using limited experimental data. A novel invariant-based model estimates unidirectional carbon fiber-reinforced polymer (CFRP) lamina fracture properties, such as ultimate strengths in longitudinal, transverse, and shear directions and intralaminar longitudinal fracture toughness. The model, developed through a comprehensive literature review of carbon/epoxy systems, significantly reduces required experimental testing by utilizing the Tsai modulus to employ stiffness properties for strength and toughness estimation. Validation through finite element analyses of open-hole tensile/compressive specimens demonstrates close agreement between predicted and experimental results. The model's unified methodology enables accurate meso-scale simulations with minimal experimental input, potentially streamlining material characterization processes in aerospace applications.