Surface and back pressures, and three aerodynamic force components for two models of reentry vehicle: the cocoon type and the pan type, were measured at three transonic flow speeds: Mach number of 0.6, 0.7 and 0.8. Schlieren photographs were also taken to visualize the flow pattern. Comparing the results of force measurement with those calculated from measured pressure distributions, reasonable agreement was obtained. The Euler equations were also solved for a case with attack angle of 0 deg and Mach number of 0.8. In spite of good agreement on pressure distribution along the forward part of model, there was some discrepancy in back pressure between numerical calculation and experiment, which produced difference in drag coefficient. When the back pressure was then replaced by the experimental data, reasonable agreement of drag coefficient was obtained between them. As a result, it turned out that the pan type was more appropriate as a reentry vehicle than the cocoon type.