A shape optimization methodology for reducing the sonic boom initial pressure rise

We present a shape optimization methodology for reducing the initial shock pressure rise (ISPR) on the ground of a supersonic aircraft. This methodology combines elements from the linearized aerodynamic theory such as Whitham's F-function with elements from the nonlinear aerodynamic theory such as the prediction of lift distribution by an Euler or a Navier-Stokes flow solver. We report on the application of this shaping technology to a Point of Departure aircraft developed by Lockheed-Martin for DARPA's Quiet Supersonic Platform program. We demonstrate a ten-fold reduction of the ISPR on the ground, from 1.623 psf at M_∞ = 1.5 to 0.152 psf, while maintaining constant lift and wave drag.