Nacelle integration with reflexed wing for sonic boom reduction

An aircraft comprising:

• a wing with a non-movable reflexed airfoil portion, wherein:
• the reflexed airfoil portion includes a convergent section thickness of the underside of the wing that begins at an intermediate location between the leading edge and the trailing edge of the wing, and extends to the trailing edge of the wing,
• the shape of the convergent section thickness is defined by at least one reflex angle, and
• the slope of the at least one reflex angle is greater than or equal to zero proximate the trailing edge of the wing.

An aircraft design system comprising:

• logic instructions operable to:
• determine the shape of a reflexed airfoil portion of a wing, wherein the reflexed airfoil portion is a convergent section thickness of the underside of the wing that begins at an intermediate location between the leading edge and the trailing edge of the wing, and extends to the trailing edge of the wing, and the shape of the convergent section thickness is formed with at least one reflex angle;
• allow the user to constrain the pressures under the reflexed airfoil portion to canceling only positive pressures;
• and
• allow the user to vary the thickness of a nacelle under the wing to meet the pressure constraint.