10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference 2004
DOI: 10.2514/6.2004-4629
|View full text |Cite
|
Sign up to set email alerts
|

Transonic Airfoil Shape Optimization in Preliminary Design Environment

Abstract: A modified profile optimization method using a smoothest shape modification strategy (POSSEM) is developed for airfoil shape optimization in a preliminary design environment. POSSEM is formulated to overcome two technical difficulties frequently encountered when conducting multipoint airfoil optimization within a high-resolution design space: the generation of undesirable optimal airfoil shapes due to high frequency components in the parametric geometry model and significant degradation in the off-design perfo… Show more

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
2
1
1
1

Citation Types

0
5
0

Year Published

2005
2005
2021
2021

Publication Types

Select...
3
3
1

Relationship

1
6

Authors

Journals

citations
Cited by 10 publications
(5 citation statements)
references
References 8 publications
0
5
0
Order By: Relevance
“…Under the circumstances where more delicate consideration needs to be put in the region with concerns (e.g., leading-edge region that is faced with coming flow), conventional CST does not always work as expected, 23 although a good design space should be equipped with capabilities to find subtle beneficial changes that are nonintuitive when starting from a baseline design. 24…”
Section: Demands For More Insights Of Cst To the Leading-edge Regionmentioning
confidence: 99%
“…Under the circumstances where more delicate consideration needs to be put in the region with concerns (e.g., leading-edge region that is faced with coming flow), conventional CST does not always work as expected, 23 although a good design space should be equipped with capabilities to find subtle beneficial changes that are nonintuitive when starting from a baseline design. 24…”
Section: Demands For More Insights Of Cst To the Leading-edge Regionmentioning
confidence: 99%
“…Thus, there are 13 design variables in total defining the geometry of the airfoil, which must be searched by the optimizer and analyzed using CFD software. It is thought that 13 is a reasonable number of variables for an airfoil design problem of this nature; it is not uncommon for such a problem to make use of 22 or more variables [16,18,19].…”
Section: A Direct Optimizationmentioning
confidence: 99%
“…The airfoil shapes are represented by NURBS curve. The basis airfoil is based on Li's [8] study but only 18 control points were selected to simplify the process. 6 out of 18 points were allowed to move within a specified range to change the airfoil shape.…”
Section: -D Airfoil Optimizationmentioning
confidence: 99%