Systems and methods for controlling a magnitude of a sonic boom

A method of controlling a magnitude of a sonic boom caused by off-design condition operation of a supersonic aircraft at supersonic speeds, the method comprising the steps of:

• applying a plurality of composite plies to a pair of swept wings joined by a center box such that an axis of greatest stiffness of each ply of the plurality of composite plies is oriented at an angle of ten to thirty degrees with respect to a rear spar of each wing of the pair of swept wings;
• attaching the pair of swept wings and the center box to the supersonic aircraft;
• operating the supersonic aircraft at supersonic speeds and at an off-design condition;
• reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies;
• and
• minimizing the magnitude of the sonic boom during off-design condition operation of the supersonic aircraft through reduction of wing twist.

A wing assembly for a supersonic aircraft, the wing assembly comprising:

• a pair of wings having a swept back configuration, each wing of the pair of wings including a surface and a rear spar;
• a center box joining each wing of the pair of wings;
• and
• a composite ply disposed on the surface of each wing, the composite ply having an axis of greatest stiffness oriented at an angle of ten to thirty degrees with respect to the rear spar of each wing,
• wherein each wing is free of any composite ply having an axis of greatest stiffness oriented in a manner that is parallel to the rear spar of each wing.