The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration

Abstract

A summary of NASA's High Speed Aeroservoelasticity (ASE) project is provided with a focus on a low-boom supersonic configuration developed by Lockheed-Martin and referred to as the N+2 configuration. The summary includes details of the computational models developed to date including a linear finite element model (FEM), linear unsteady aerodynamic models, structured and unstructured CFD grids, and discussion of the FEM development including sizing and structural constraints applied to the N+2 configuration. Linear results obtained to date include linear mode shapes and linear flutter boundaries. In addition to the tasks associated with the N+2 configuration, a summary of the work involving the development of AeroPropulsoServoElasticity (APSE) models is also discussed.

Computational Aeroelastic Analyses of a Low-Boom Supersonic Configuration

“…The ultimate goal of this development is to be able to determine if the airframes flexibility has an effect on the thrust dynamics of the propulsion system, coupling back to the airframe flexibility modes as a closed loop system, in order to study performance like vehicle stability and ride quality. This paper will address results from prior publications [10,11] as well as recent accomplishments. The paper begins with a description of the Lockheed-Martin N+2 configuration followed by a description of the structural sizing and analysis leading to an FEM.…”

“…Recent and updated linear aeroelastic analyses are presented as well. The vehicle design, sizing, FEM analyses/parametrics, linear aeroelastic analyses, and CFD loads analyses were performed by Lockheed-Martin [10,11]. Unstructured grids of the N+2 configuration, generated at NASA, are presented along with Euler (inviscid) static aeroelastic and sonic boom propagation results at a cruise condition.…”

An Overview of the NASA High Speed ASE Project: Aeroelastic Analyses of a Low-Boom Supersonic Configuration

“…The ultimate goal of this development is to be able to determine if the airframes flexibility has an effect on the thrust dynamics of the propulsion system, coupling back to the airframe flexibility modes as a closed loop system, in order to study performance like vehicle stability and ride quality. This paper will address recent results not covered in the initial work by Silva et al [10]. The paper begins with a description of the N+2 configuration followed by a description of the structural sizing and analysis leading to a finite element model (FEM).…”

Using FUN3D for Aeroelatic, Sonic Boom, and AeroPropulsoServoElastic (APSE) Analyses of a Supersonic Configuration

“…This paper presents a status update on this computational effort. 1,2 This includes a description of the N+2 configuration and a summary of the Lockheed-Martin finite element model (FEM). Euler (inviscid) and Navier-Stokes (viscous) results that address the effect of static aeroelastic deformation on sonic boom propagation are presented.…”