Optimization procedure with analytical aerodynamic sensitivity for reduced sonic boom design

Abstract

A design optimization procedure for improved sonic boom and aerodynamic performance of highspeed aircraft has been developed. The multiobjective optimization procedure simultaneously minimizes the primary sonic boom and the drag-to-lift ratio of the aircraft. Constraints are imposed on the secondary sonic boom and lift coefficient. The flow equations are solved using the three-dimensional parabolized Navier-Stokes solver, and sonic boom analysis is performed using an extrapolation procedure. A nonlinear programming technique and an approximate analysis procedure are used in the optimization. An efficient, semianalytical sensitivity analysis technique is used to calculate the aerodynamic and sonic boom design sensitivities. The optimization procedure and sensitivity analysis technique are applied to two high-speed wing body configurations (delta wing and doubly swept wing). Results obtained in both cases show improvements in the sonic boom pressure peaks and aerodynamic performance of the aircraft. The tradeoff between the sonic boom and aerodynamic performance of the aircraft is brought out by the reductions in the lift of the optimum configurations associated with the reductions in the second pressure peak of their sonic boom signatures.