Inverse Design Approach for Low-Boom Supersonic Configurations

Abstract

The shaped sonic boom theory is a valuable, efficient, computationally economical and robust tool in preliminary design of low-boom aircraft configurations. Instead of introducing a new F-function parameterization, as it has been investigated already in the past, the paper adopts a more general formulation proposed in the literature and focuses on reducing the limitations of the inverse method in the design process. Three main contributions are proposed: 1) a revisited procedure based on optimization to solve the coefficients of the F-function that enables to switch between different parameterizations; 2) a definition of the geometry corresponding to the equivalent area distribution combined with a fuselage tailoring process based on direct shape optimization; 3) a strategy to introduce a generic acoustic metrics in the definition of an optimum F-function. The proposed strategy enables the designer to evaluate the geometry of a low-boom configuration that corresponds to a desired F-function in a complete inverse design approach. In this way, the usual limits of the inverse method are significantly alleviated by the present method.

Effects of Atmospheric Profiles on Sonic Boom Perceived Level from Supersonic Vehicles

“…Current findings promote continued research into aircraft concepts capable of lower booms across a large range of atmospheric conditions, either via careful aircraft geometry design [44,45] or the incorporation of condition-specific adaptations. While shock waves are inherent to supersonic flight and cannot be eliminated, the ground pressure distribution can be modified by varying the aircraft geometry [46].…”

Illustrations of multi-disciplinary high-fidelity analysis capabilities for aero-structural and aero-acoustic aircraft design

“…Based on existing market studies [22], recent and ongoing studies in industry and academia [23][24][25] [26][27] [28] (and a large a priori), the following Top Level Aircraft Requirements (TLAR) have been selected for this design studies:  a range of 5000 Nm,  a payload 16.000 lb (~80 pax),…”

A low-boom and low-drag design method for supersonic aircraft and its applications on airfoils

“…For reducing the drag resulting from the blunt nose shape, Darden [20] modified and controlled the bluntness of the area distribution near the nose and further developed this minimization method. The inverse design approaches have been widely adopted for the low-boom supersonic configurations [21,22]. This approach mainly designates a target near-field or far-field pressure signature and achieves it by shaping the aircraft.…”