Transition location can be a significant source of uncertainty in high-speed vehicle drag and heating predictions. Also, the efficacy of transition control depends largely on where transition is predicted. Because of facility noise, transition measurements in ground-test facilities are generally not reliable predictors of flight performance and we must rely on computational approaches for design for flight. The program at Arizona State University to investigate stability and transition of hypersonic boundary-layer flows has been ongoing for several years. In this final report we compile the significant theoretical and computational results from this program. The research has progressed through several logical steps with increasing complexity: Linear stability theory with the effects of chemistry and bow shock on a sharp circular cone at zero incidence with a PNS basic state. Examine 3-D effects on a sharp elliptic cone at zero incidence with a PNS basic state. Include nose bluntness (entropy layer and curved shock) plus nonequilibrium chemistry on a circular cone in the nonlinear Stability Equations with a Navier-Stokes basic state. Provide a new crossflow Reynolds number including compressibility and wall-temperature effects for use in conceptual design.