Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

20000061431 Defence Evaluation Research Agency, UK
The Application of Pareto Frontier Methods in the Multidisciplinary Wing Design of a Generic Modern Military Delta
Aircraft
Fenwick, Steven V., Defence Evaluation Research Agency, UK; Harris, John C., Defence Evaluation Research Agency, UK; Aerodynamic
Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June 2000, pp. 13-1 -
13-7; In English; See also 20000061419; Copyright Waived; Avail: CASI; A02, Hardcopy
As a partner in the EC Framework IV ”FRONTIER” project, DERA has investigated the application of a genetic algorithm
(GA) and Pareto frontier methods to optimize the trade-off between multiple design objectives. A Pareto frontier is defined as
the limit of design space beyond which one attribute of a design cannot be improved without detriment to another. DERA has
applied the software produced within the project to the multidisciplinary design of the wing of a generic modern military delta
aircraft, to trade-off the conflicting design requirements of range and agility. This paper recounts DERA’s experience of the methods
as an approach to the solution of a trial multidisciplinary design and optimisation (MDO) problem together with some of the
results produced. Details of the software produced within the project are provided, along with conclusions and recommendations
from its use.
Author
Wings; Design Analysis; Computer Design; Genetic Algorithms
20000061436 Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Inst. of Design Aerodynamics, Brunswick, Germany
A System for the Aerodynamic Optimization of Three-Dimensional Configurations
Orlowski, M., Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Germany; Tang, W., Deutsche Forschungsanstalt fuer Luftund
Raumfahrt, Germany; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment;
June 2000, pp. 19-1 - 19-13; In English; See also 20000061419; Copyright Waived; Avail: CASI; A03, Hardcopy
The paper presents a system for the aerodynamic optimization of three-dimensional configurations. This system is based on
the repeated calculation of the flowfield around three-dimensional geometries by solving the Euler/Navier-Stokes equations. The
basic structure of the system and the incorporated modules are described. Under the same conditions the system must provide the
same solutions of classic aerodynamic optimization problems as given in literature. So the function of the system is checked with
the Rhombus airfoil and the Sears-Haack body. The potential of the system is demonstrated with current aerodynamic optimization
problems.
Author
Aerodynamic Configurations; Optimization; Three Dimensional Models
20000061437 Alenia Spazio S.p.A., Divisione Aeronautica, Turin, Italy
Alenia Multidisciplinary Design Optimisation: Topics and Approaches
Selmin, V., Alenia Spazio S.p.A., Italy; Vitagliano, P. O., Alenia Spazio S.p.A., Italy; Pennavaria, A., Alenia Spazio S.p.A., Italy;
Crosetta, L., Alenia Spazio S.p.A., Italy; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary
Environment; June 2000, pp. 20-1 - 20-6; In English; See also 20000061419
Contract(s)/Grant(s): CEC-BE95-2056; Copyright Waived; Avail: CASI; A02, Hardcopy
The purpose of this paper is to report on methods which have been developed or which are under development at Alenia Aeronautica
for multidisciplinary optimum design, with particularly emphasis on aerodynamic shape design. Results of transonic 2D
and 3D optimisation problems are presented.
Author
Optimization; Design Analysis; Two Dimensional Models; Three Dimensional Models
20000061438 Instituto Nacional de Tecnica Aeroespacial, Fluid Dynamics Dept., Madrid, Spain
Design and Optimization of Wings in Subsonic and Transonic Regime
Monge, Fernando, Instituto Nacional de Tecnica Aeroespacial, Spain; Jimenez-Varona, Jose, Instituto Nacional de Tecnica Aeroespacial,
Spain; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June
2000, pp. 21-1 - 21-10; In English; See also 20000061419; Copyright Waived; Avail: CASI; A02, Hardcopy
For a realistic and practical aerodynamic optimization the most appropriate combination of the three sets of tools taking part
in the process should be carefully studied. That is, the optimization should allow an easy implementation of constraints, and should
be multipoint without the need to prescribe pressure distributions in the objective function; the design space should be broad
enough; and the analysis tool should be fast and robust. Taking into account these criteria, a code for multipoint design and optimization
of wings in subsonic and transonic regime has been developed and will be described in this paper. The objective can be
any combination of the global aerodynamic coefficients, and geometrical and physical constraints can be applied. Results for sub-
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