Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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COMPUTER PROGRAMMING AND SOFTWARE
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20000061434 Rensselaer Polytechnic Inst., Mechanical Engineering, Aeronautical Engineering and Mechanics, Troy, NY USA
Soft Computing in Multidisciplinary Aerospace Design: New Directions for Research
Hajela, Prabhat, Rensselaer Polytechnic Inst., USA; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent
Multi-Disciplinary Environment; June 2000, pp. 17-1 - 17-13; In English; See also 20000061419; Copyright Waived; Avail:
CASI; A03, Hardcopy
There has been increased activity in the study of methods for multidisciplinary analysis and design. This field of research
has been a busy one over the past decade, driven by advances in computational methods and significant new developments in
computer hardware. There is a concern, however, that while new computers will derive their computational speed through parallel
processing, current algorithmic procedures that have roots in serial thinking are poor candidates for use on such machines - a paradigm
shift is required! Among new advances in computational methods, soft computing techniques have enjoyed a remarkable
period of development and growth. of these, methods of neural computing, evolutionary search, and fuzzy logic have been the
most extensively explored in problems of multidisciplinary analysis and design. The paper will summarize important accomplishments
to-date, of neurocomputing, fuzzy-logic, and evolutionary search, including immune network modeling, in the field of multidisciplinary
aerospace design.
Author
Algorithms; Computation; Fuzzy Systems; Aircraft Design; Hardware
20000061451 DaimlerChrysler Aerospace A.G., Ottobrun, Germany
Rapid Generation of Conceptual and Preliminary Design Aerodynamic Data by a Computer Aided Process
Fornasier, Luciano, DaimlerChrysler Aerospace A.G., Germany; Gottmann, Thomas, DaimlerChrysler Aerospace A.G., Germany;
Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June 2000, pp.
35-1 - 35-11; In English; See also 20000061419; Sponsored in part by the JULIUS partners; Copyright Waived; Avail: CASI; A03,
Hardcopy
A multidisciplinary integration framework (MIDAS- an acronym for Multidisciplinary Integration for Design and Analysis
Software) is developed for a quick and accurate assessment of aircraft performance. The system allows for the continues integration
of the conceptual and preliminary design stages. The MIDAS system is starting from the definition of the configuration layout
to provide basic aerodynamic data- for performance analysis, sizing, structural layout and early handling qualities. The first aerodynamic
dataset is provided by an Excel-based module in a highly automated way. This data base can be updated by computational
and experimental fluid dynamics findings. Another MIDAS module integrate the preparation of CFD meshes. The paper deals
with the integration of aerodynamic methods within the aircraft design.
Author
Aircraft Design; Computer Aided Design; Computer Techniques; Reliability Analysis
20000062014 NASA Glenn Research Center, Cleveland, OH USA
National Combustion Code: Parallel Implementation and Performance
Quealy, A., DYNACS Engineering Co., Inc., USA; Ryder, R., Flow Parametrics, LLC, USA; Norris, A., NASA Glenn Research
Center, USA; Liu, N.-S., NASA Glenn Research Center, USA; April 2000; 16p; In English; 38th; Aerospace Sciences, 10-13 Jan.
2000, Reno, NV, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA
Contract(s)/Grant(s): RTOP 509-10-24
Report No.(s): NASA/TM-2000-209801; E-12106; NAS 1.15:209801; AIAA Paper 2000-0336; No Copyright; Avail: CASI;
A03, Hardcopy; A01, Microfiche
The National Combustion Code (NCC) is being developed by an industry-government team for the design and analysis of
combustion systems. CORSAIR-CCD is the current baseline reacting flow solver for NCC. This is a parallel, unstructured grid
code which uses a distributed memory, message passing model for its parallel implementation. The focus of the present effort has
been to improve the performance of the NCC flow solver to meet combustor designer requirements for model accuracy and analysis
turnaround time. Improving the performance of this code contributes significantly to the overall reduction in time and cost of
the combustor design cycle. This paper describes the parallel implementation of the NCC flow solver and summarizes its current
parallel performance on an SGI Origin 2000. Earlier parallel performance results on an IBM SP-2 are also included. The perfor-
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