A two-phase study is described that designs and validates a supersonic airliner feasible for entry into service in the 2018 to 2020 timeframe (NASA N+2 generation). A Mach 1.6 to 1.8 low sonic-boom aircraft configuration is developed that meets aggressive sonic-boom and performance goals. The concept and the tools utilized for its design are validated through a series of wind-tunnel tests at the NASA Ames 9 ft x 7 ft Supersonic Wind Tunnel, NASA Ames 11 ft Transonic Wind Tunnel, and NASA Glenn 8 ft x 6 ft Supersonic Wind Tunnel. Comparisons between CFD and wind-tunnel near-field pressure distributions are made. Sonic-boom test techniques are described and investigated. Results from spatial-averaging show the best agreement with CFD.

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