Transonic Airfoil Shape Optimization in Preliminary Design Environment

2006 ◽  
Vol 43 (3) ◽  
pp. 639-651 ◽  
Author(s):  
W. Li ◽  
S. Krist ◽  
R. Campbell
Keyword(s):  
Shape Optimization ◽  
Preliminary Design ◽  
Design Environment ◽  
Transonic Airfoil

AN OPTIMIZATION MODEL FOR PRELIMINARY STABILITY AND CONFIGURATION ANALYSES OF SEMI-SUBMERSIBLES

2021 ◽  
Vol 159 (A3) ◽  
Author(s):  
G D Gosain ◽  
R Sharma ◽  
Tae-wan Kim
Keyword(s):  
Optimization Model ◽  
Design Method ◽  
Optimization Techniques ◽  
Design Approach ◽  
Preliminary Design ◽  
Design Environment ◽  
Preliminary Stage ◽  
Steel Weight ◽  
Motion Characteristics ◽  
Almost All

In the modern era of design governed by economics and efficiency, the preliminary design of a semi-submersible is critically important because in an evolutionary design environment new designs evolve from the basic preliminary designs and the basic dimensions and configurations affect almost all the parameters related to the economics and efficiency (e.g. hydrodynamic response, stability, deck load and structural steel weight of the structure, etc.). The present paper is focused on exploring an optimum design method that aims not only at optimum motion characteristics but also optimum stability, manufacturing and operational efficiency. Our proposed method determines the most preferable optimum principal dimensions of a semi-submersible that satisfies the desired requirements for motion performance and stability at the preliminary stage of design. Our proposed design approach interlinks the mathematical design model with the global optimization techniques and this paper presents the preliminary design approach, the mathematical model of optimization. Finally, a real world design example of a semi-submersible is presented to show the applicability and efficiency of the proposed design optimization model at the preliminary stage of design.

A Knowledge Based Geometric Modeling System for Preliminary Design Using Object-Oriented Approach

1989 ◽  
Author(s):  
S. Akagi ◽  
K. Fujita
Keyword(s):  
Geometric Modeling ◽  
Geometric Model ◽  
Object Oriented ◽  
Object Oriented Programming ◽  
Preliminary Design ◽  
Design Environment ◽  
Knowledge Based ◽  
Object Oriented Approach ◽  
Geometric Modeling System ◽  
Oriented Approach

Abstract A knowledge-based geometric modeling system for preliminary design was developed using object-oriented approach. Three types of knowledge for design, i.e. the model representing a design product including the geometric model, the procedures manipulating the design product and the knowledge managing the design process were integrated in the system. The model built up with object-oriented programming provides an effective and flexible design environment. Finally, the system was applied to the preliminary design of a ship’s hull arrangement to ascertain its validity and effectiveness.

A multi-disciplinary toolbox for rotorcraft design

2018 ◽  
Vol 122 (1250) ◽  
pp. 620-645 ◽  
Author(s):  
P. Weiand ◽  
A. Krenik
Keyword(s):  
Design Process ◽  
Distributed Computation ◽  
Fundamental Concept ◽  
Software Framework ◽  
Preliminary Design ◽  
Main Rotor ◽  
Design Environment ◽  
High Level ◽  
Different Levels

ABSTRACTThe purpose of this paper is to outline the structure of the DLR integrated rotorcraft design process. The complexity of rotorcraft design requires the development of the tools directly by the specialists of the respective institutes, where the tools are continuously refined and published to authorised users. The integration of the tools into a suitable software framework by means of distributed computation and the harmonisation of the tools among each other are presented. This framework delivers a high level of modularity making the layout and testing of the process very flexible. This design environment covers the conceptual and preliminary design phases. Not only conventional main/tail rotor configurations can be designed, but also some other configurations with more than one main rotor. The fundamental concept behind the layout of the tools is demonstrated, especially the use of scaling and optimisation loops in connection with the different levels of fidelity and the different phases of design.

Aerodynamic wing shape optimization based on the computational design framework CEASIOM

2017 ◽  
Vol 89 (2) ◽  
pp. 262-273 ◽  
Author(s):  
Mengmeng Zhang ◽  
Arthur Rizzi
Keyword(s):  
Shape Optimization ◽  
Collaborative Design ◽  
Optimization Technique ◽  
Computational Design ◽  
Optimization Methods ◽  
Wing Shape ◽  
Design Framework ◽  
Design Environment ◽  
Sequential Approach ◽  
Content Type

Purpose A collaborative design environment is needed for multidisciplinary design optimization (MDO) process, based on all the modules those for different design/analysis disciplines, and a systematic coupling should be made to carry out aerodynamic shape optimization (ASO), which is an important part of MDO. Design/methodology/approach Computerized environment for aircraft synthesis and integrated optimization methods (CEASIOM)-ASO is developed based on loosely coupling all the existing modules of CEASIOM by MATLAB scripts. The optimization problem is broken down into small sub-problems, which is called “sequential design approach”, allowing the engineer in the loop. Findings CEASIOM-ASO shows excellent design abilities on the test case of designing a blended wing body flying in transonic speed, with around 45 per cent drag reduction and all the constraints fulfilled. Practical implications Authors built a complete and systematic technique for aerodynamic wing shape optimization based on the existing computational design framework CEASIOM, from geometry parametrization, meshing to optimization. Originality/value CEASIOM-ASO provides an optimization technique with loosely coupled modules in CEASIOM design framework, allowing engineer in the loop to follow the “sequential approach” of the design, which is less “myopic” than sticking to gradient-based optimization for the whole process. Meanwhile, it is easily to be parallelized.

Axial Compressor Aerodesign Evolution at General Electric

2002 ◽  
Vol 124 (3) ◽  
pp. 321-330 ◽  
Author(s):  
Leroy H. Smith,
Keyword(s):  
State Of The Art ◽  
Axial Compressor ◽  
Prediction Method ◽  
Design System ◽  
Preliminary Design ◽  
Vector Diagram ◽  
Equilibrium Solutions ◽  
Detailed Design ◽  
The 1960S ◽  
Transonic Airfoil

This paper traces the origins of the GE Design System and how it has evolved from early methods to underlie and supplement present CFD methods, which are not themselves discussed herein. The two main elements of the detailed aero design process are vector diagram establishment and airfoil design. Their evolution is examined, and examples of how they were used to design some early GE compressors of interest are given. By the late 1950s, some transonic airfoil shapes were being custom tailored using internal blade station data from more complete radial equilibrium solutions. In the 1960s, rules for shaping transonic passages were established, and by the 1970s, custom tailoring was done for subsonic blading as well. The preliminary design layout process for a new compressor is described. It involves selecting an annulus shape and blading overall proportions that will allow a successful detailed design to follow. This requires establishment of stage loading limits that permit stall-free operation, and an efficiency potential prediction method for state-of-the-art blading. As design methods evolved, the newer approaches were calibrated with data-match experience, a process that is expected to always be needed.

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