With the aims of creating and validating innovative fundamental technologies for highspeed atmospheric flights, a small scale supersonic experiment vehicle is designed as a flying test bed. Several aerodynamic configurations are proposed and analyzed by wind tunnel tests. A twin-engine configuration is selected as the baseline. Its flight capability is predicted by point mass analysis on the basis of aerodynamic characterization and propulsion performance estimation. In addition, a prototype vehicle with the equivalent configuration and dimension is designed and fabricated for verification of the subsonic flight characteristics of the experiment vehicle. Its first flight test is carried out and good flight capability is demonstrated. © 2011 by Kazuhide Mizobata.