(See the write up under the SPACESHIPONE GROUND TEST section that describes our Ford-250 wind tunnel which was used to help derive the current flight configuration). Other test objectives included a functional check of the rocket motor controller, ARM, FIRE and safing switches as well as the oxidizer dump valve. Additional planned maneuvers included full rudder pedal sideslips and more aggressive nose pointing while in the feathered configuration. Results: Launch conditions were 46,200 feet and 115 knots and produced a clean separation. The tail performance was examined by flying "longitudinal stability" points between stall and 130 knots and showed considerable improvement of the airfoil's lift coefficient as well as its post stall characteristics. No vehicle pitch up tendency was noted as the main wing now stalls first. Real time video of the tufted tails fed back down to mission control helped considerably in assessing the performance of these aerodynamic improvements. More aggressive maneuvering in the feather made it evident that the pilot could readily point the vehicle's nose where desired and all rocket motor functionality tests were satisfactory.
Flight Time: 1.1 hours/ 17 mins 49 secs White Knight Pilot: Siebold White Knight Copilot: Bird White Knight Flt Engineer: Moore SpaceShipOne Pilot: Melvill High Chase-Starship Pilot: Binnie Low Chase-Extra Pilot: Coleman