Zero Lift Drag and Drag Divergence Prediction for Finite Wings in Aircraft Design

This paper reviews the basis of current methods used for the calculation of zero-lift drag and drag divergence Mach number and proposes an improved set of methods. The majority of past methods are based on profile considerations alone and, at most, limited wing parameters. These methods are reviewed and compared for their applicability to the low aspect ratio and highly swept wing configurations that are being considered for many future aircraft. Based on the limitations of current methods, a new technique comprising a vortex lattice solution coupled to a profile boundary layer analysis is developed. Using results from this new method, metamodels are created that are applicable for inclusion in aircraft sizing and synthesis codes for conceptual and preliminary aircraft design.