A waverider designed for Mach 14 flight is numerically simulated using the University of Minnesota US3D computational fluid dynamics code. Numerical results are compared with experimental data provided by the Arnold Engineering Development Center Hypervelocity Wind Tunnel Number 9. Two sets of nominal Mach 8 flight conditions are examined, with a low Reynolds number of 14 million/m and a high Reynolds number of 54 million/m. Pitch angle sweeps in the range of -10° to 5° are presented for both cases. Very good agreement between numerical simulation and experimental measurement is shown in plots of lift-to-drag ratio vs. alpha, lift and drag coefficients vs. alpha, and pitch moment coefficient vs. alpha. In addition, direct comparisons are made for the complete set of discrete pressure taps and heat transfer probes.