This paper details the aerodynamic design of the 2008 - 2009 University of Colorado Design, Build, Fly (DBF) team's flying wing aircraft. Given the inherent problems of a flying wing, namely the longitudinal stability difficulties and relative lack of information available, the team's success in designing and developing a stable and unique aircraft with the help of various analysis tools is documented to increase the knowledge base for future projects. The selection of an initial aircraft geometry that include wing area (S), aspect ratio (AR), sweep angle (Λ) and taper ratio (λ), given competition-restricted aircraft dimensions and design requirements, is explained. The effect of varying sweep angles and taper ratios on aircraft stability is analyzed. Analysis shows the optimal combination of leading edge sweep angle and taper ratio that meets all top level requirements is 23 degrees and 0.5, respectively. Large databases of airfoils are used to find airfoils with low moment coefficients. The HS602 and HS520 airfoils are combined spanwise to produce an aerodynamic twist with desirable aerodynamic characteristics. Once level flight stability is theoretically achieved for symmetric underwing payload loading cases, asymmetric loading cases are evaluated for stability during normal flight conditions and takeoff using rudder, aileron, and elevator deflections in Athena Vortex Lattice (AVL). After stability is determined in all loading cases, the root locus of the aircraft is calculated to assess the lateral and longitudinal stability modes using the linearized equations of motion, which shows the chosen design is stable and controllable. Finally, the CFD program PowerFLOW shows the lift and drag characteristics of the designed aircraft to verify that the thrust provided overcomes the drag experienced in flight. With this final requirement met, all analysis theoretically verifies that the team's flying wing will meet the requirements imposed on its design by the DBF competition.