FUSELAGE SHAPING ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM

摘要

Method and apparatus for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft including configuring the aircraft so that in flight, with landing gear retracted, a lower profile of the aircraft is substantially linear or slightly concave downward. A nose portion of the aircraft is arranged so that an apex thereof is coincident with the lower profile of the aircraft. The aircraft is flown at supersonic speed and oriented during supersonic flight so that the substantially linear lower profile of the aircraft is oriented substantially parallel to onset airflow. Weak pressure disturbances are generated below the aircraft, and waves thereof are radiated below the aircraft toward the ground. These disturbances below the aircraft are of lesser magnitude than pressure disturbances simultaneously generated and radiated above the aircraft. The weak pressure disturbances generated below the aircraft are controlled so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during supersonic flight. In a second aspect, a retractable spike is included at the nose or rear of the aircraft for minimizing sonic boom effects at ground level during supersonic flight.