(57) ABSTRACT A method for integrating an engine nacelle beloW the Wing of a supersonic
aircraft With loW sonic boom capabilities includes determining the shape of a re? exed …

(57) ABSTRACT A method and design System for a low drag Vehicle includes determining a
plurality of configurations for at least two different Mach numbers that minimize the rate of …

AS a sonic boom pressure wave propagates to the ground, it transits through three fields [1].
As shown in Fig. 1, the near field is the region from the aircraft to several body lengths away …

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 …

This paper describes a computational method for the analysis and mitigation via shape
optimization of the sonic boom associated with supersonic flight. The method combines a …

This thesis is concerned with the development of a multidisciplinary optimization framework
for the design of aircraft accounting for fluid-structure and fluid-acoustic coupling effects. The …

A multi-level framework for the design of low sonic boom aircraft is presented. An approach
combining linear supersonic potential theory with atmospheric propagation and loudness …

TYPICALLY, in the preliminary design stage, designers validate key aerodynamic
performance parameters by conducting windtunnel tests [1]. When designing a supersonic …

The role of INRIA in HISAC is to contribute to the developement of methods for the
simulation and reduction of sonic boom. The contribution of INRIA to Task 2.3. 2 concerns …

Euler-based boom reduction: INRIA contribution to HISAC 2.3. 2 Workshop Saint-Cloud, June
2006 - Archive ouverte HAL Accéder directement au contenu Documentation FR Français (FR) …