Inverse Design Approach for Low-Boom Supersonic Configurations
نویسندگان
چکیده
منابع مشابه
Interactive Inverse Design Optimization of Fuselage Shape for Low-Boom Supersonic Concepts
There are several research papers on how to design a supersonic configuration that has desirable low-boom characteristics as determined by the Seebass-George-Darden boom minimization theory (SGD theory). The low-boom signatures predicted by the SGD theory could be realized by wing-fuselage configurations. However, for a given low-boom signature generated by the SGD theory, it is still an open q...
متن کاملMultifidelity Design Optimization of Low-Boom Supersonic Jets
The practical use of high-fidelity multidisciplinary optimization techniques in low-boom supersonic business-jet designs has been limited because of the high computational cost associated with computational fluid dynamics-based evaluations of both the performance and the loudness of the ground boom of the aircraft. This is particularly true of designs that involve the sonic boom loudness as eit...
متن کاملMulti-Fidelity Design Optimization of Low-Boom Supersonic Business Jets
The practical use of high-fidelity multidisciplinary optimization techniques in low-boom supersonic business jet designs has been limited because of the high computational cost associated with CFD-based evaluations of both the performance and the loudness of the ground boom of the aircraft. This is particularly true of designs that involve the sonic boom loudness as either a cost function or a ...
متن کاملResponse Surface Methodologies for Low-Boom Supersonic Aircraft Design using Equivalent Area Distributions
The use of response surface models (also known as surrogate models) to describe the performance of aerospace systems within a given design space is by now fairly well established in the MDO community. Despite such widespread use, surrogate-based optimization techniques can incur significant computational expense when high-dimensional spaces must be modeled. In this paper we describe an adaptive...
متن کاملAdjoint-Based Sonic Boom Reduction for Wing-Body Configurations in Supersonic Flow
This paper presents an adjoint method for the calculation of remote sensitivities in supersonic flow. The goal is to develop a set of adjoint equations and their corresponding boundary conditions to quantify the influence of geometry modifications on the pressure distribution at an arbitrary location within the domain of interest, away from the surface of the aircraft. First, this paper present...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: AIAA Journal
سال: 2014
ISSN: 0001-1452,1533-385X
DOI: 10.2514/1.j052834