Hypersonic flows over simple 3-D bodies and a space vehicle are simulated using a real-gas Navier-Stokes code under an equilibrium air assumption. This code is based on 3-D upwind flux splitting scheme with generalized Roe's Riemann solver. The real-gas effect is incorporated using the VEG (Variable Equivalent Gamma) method. The equivalent gamma and other thermodynamic properties are calculated using empirical curve fits. Numerical simulations are conducted for flow fields around a spherical blunt body, a spherical-nose cylinder, and a cone-cylinder as simple configurations, and HOPE (H-orbiting plane: Japanese spaceplane) as a practical plane configuration. Flow conditions are Mach numbers of 7.72, 15.0 for the blunt bodies, 6.86 for the cone-cylinder, and 15.0 for the HOPE. Computed pressure and density distributions are presented. Results for simple configuration cases are compared with experimental data for the code validation.