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A system and method for configuring an aircraft for low sonic boom supersonic flight conditions includes redistributing lift of a wing by configuring the wing with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled t

A system and method for configuring an aircraft for low sonic boom supersonic flight conditions includes redistributing lift of a wing by configuring the wing with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to account for the equivalent area reduction due to excursions below to goal curve. A relaxed constraint allows the equivalent area distribution of the aircraft to be at or below the equivalent area distribution goal curve to enable multiple parameters to be configured to meet the equivalent area distribution constraint, as well as other constraints. The system and method can be adapted to aid in the design of any type of vehicle whose surfaces are subject to supersonic fluid flow, especially to reduce sonic boom.

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1. A method for configuring an aircraft for low sonic boom supersonic flight conditions comprising: scaling by a computer an equivalent area distribution curve of the aircraft to approximate an ideal equivalent area distribution goal curve; andrelaxing by a computer a design constraint that requires

1. A method for configuring an aircraft for low sonic boom supersonic flight conditions comprising: scaling by a computer an equivalent area distribution curve of the aircraft to approximate an ideal equivalent area distribution goal curve; andrelaxing by a computer a design constraint that requires the equivalent area distribution curve of the aircraft to be less than or equal to (≦) the equivalent area distribution goal curve instead of equal (=) to the equivalent area distribution curve; anddetermining by a computer an optimum configuration according to at least one of: lift-to-drag ratio and low sonic boom. 2. The method according to claim 1 further comprising: segmenting by a computer a wing of the aircraft into panels;analyzing by a computer the flow characteristics for each panel; andsmoothing by a computer the configuration of each panel with adjacent panels along the span and the chord of the wing to smooth the wing surface. 3. The method according to claim 1 further comprising: determining by a computer design variables at the root and the tip of a wing of the aircraft along Mach angle lines (X−Beta*R). 4. The method according to claim 3 further comprising: limiting by a computer the length of the excursion of the equivalent area distribution curve below the equivalent area distribution goal curve by dividing the excursion into at least two smaller excursions. 5. The method according to claim 3 further comprising: analyzing by a computer the sonic boom disturbance below and to the side of the aircraft; andperturbing by a computer aircraft design variables to meet sonic boom constraints below and to the side of the aircraft. 6. The method according to claim 1 further comprising: determining by a computer an incidence angle for a wing root of the aircraft for maximum lift-to-drag and connection to a fuselage; anddetermining by a computer the shape of the remaining portions of the wing for maximum lift-to-drag. 7. The method according to claim 6 further comprising: re-determining by a computer the incidence angle for the root of a wing of the aircraft and the remaining portion of the wing to meet less than or equal to equivalent area low sonic boom constraints and maximum lift-to-drag. 8. The method according to claim 1 further comprising: dividing by a computer a flight regime of the aircraft into multiple flight modes;determining by a computer an optimum configuration of non-moving components for one of the flight modes; anddetermining by a computer an optimum configuration of moving components for the other flight modes based on the configuration of non-moving components. 9. The method according to claim 1 further comprising: determining by a computer a minimized sonic boom disturbance of an F-function; andscaling by a computer the equivalent area distribution goal curve to maintain the desired aircraft weight while countering excursions below the equivalent area distribution goal curve. 10. The method according to claim 1 further comprising: adjusting by a computer the configuration of a wing on the aircraft to redistribute areas of lift on the wing; andreshaping by a computer a fuselage of the aircraft in combination with the wing to match the equivalent area distribution goal curve. 11. The method according to claim 10 further comprising: redistributing by a computer the areas of lift subject to center-of-pressure constraints to achieve desired balance characteristics for the aircraft. 12. A method for configuring an aircraft for supersonic flight with low shock wave disturbance constraints comprising: redistributing by a computer lift of a wing by configuring the wing with areas of far-field expansion ahead of areas of far-field compression; and scaling by a computer an equivalent area distribution goal curve to maintain the desired aircraft weight while countering excursions below the equivalent area distribution goal curve. 13. The method according to claim 12 further comprising: segmenting by a computer the wing into panels;analyzing by a computer the flow characteristics for each panel; andinterpolating by a computer the configuration of each panel with adjacent panels to smooth oscillations in the wing surface chordwise, and spanwise along Mach angle lines. 14. The method according to claim 12 further comprising: analyzing by a computer perturbations of design variables at the root and the tip of the wing along Mach angle lines. 15. The method according to claim 12 further comprising: analyzing by a computer perturbations of design variables along a mid-section portion of the wing. 16. The method according to claim 12 further comprising: determining by a computer an incidence angle for the wing for maximum lift-to-drag; anddetermining by a computer the shape of the remaining portions of the wing for maximum lift-to-drag; andre-determining by a computer the incidence angle and shape of the wing to also meet low sonic boom constraints. 17. The method according to claim 12 further comprising: redistributing by a computer the lift of the wing with center-of-pressure constraints for aircraft balance. 18. The method according to claim 12 further comprising: dividing by a computer a flight regime of the aircraft into multiple flight modes;determining by a computer an optimum configuration according to sonic boom constraints at a flight condition; anddetermining by a computer another optimum configuration to minimize drag at another flight condition subject to sonic boom constraints. 19. The method according to claim 12 further comprising: dividing by a computer the areas of far-field expansion and far-field compression into at least two areas of expansion and compression to reduce the magnitude of the sonic boom disturbance. 20. The method according to claim 12 further comprising: determining by a computer a desired magnitude of sonic boom disturbance on an F-function; andscaling by a computer the equivalent area distribution goal curve to maintain the desired aircraft weight while countering excursions below the equivalent area distribution goal to achieve the desired magnitude of sonic boom disturbance. 21. The method according to claim 12 further comprising: analyzing by a computer the sonic boom disturbance below and to the side of the aircraft; andconfiguring by a computer the aircraft to meet sonic boom constraints below and to the side of the aircraft. 22. The method according to claim 12 further comprising: allowing the user to define a design variable by a computer with limits that allow variation in the incidence angle of the wing where the wing joins the aircraft within a range that allows the wing to be connected to the aircraft.