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Efficient Design Optimization of Vortex Generators in Subsonic Offset Inlet by Discrete Adjoint Approach

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Authors
Yi, JunSok; Lee, Byung Joon; Kim, Chongam
Issue Date
2011-06
Publisher
AIAA
Citation
20th AIAA Computational Fluid Dynamics Conference, 2011-3535, pp. 1-22
Keywords
공학
Abstract
This paper deals with the adjoint-based design optimization of vortex generators for the
performance improvement of the subsonic inlet. The RAE M2129, an S-shaped inlet, was
selected as the target geometry. Because of the differences in radius of curvature between the
port side (outer wall) and starboard side (inner wall), a centrifugal pressure gradient that
induces circulatory flow and secondary flow was developed. To minimize these detrimental
aerodynamic phenomena, a design optimization of vortex generators installed in subsonic
inlet was conducted. To maximize the flow quality enhancement, the effectiveness and
position of vortex generator are independently optimized by using the design parameters of
height, chord length, angle of incidence, axial position, and the circumferential position of
each vortex generator. To increase the design efficiency, the source term model of vortex
generator was employed instead of the gridded vortex generator. Since the original source
term model cannot reflect a small change in position and has difficulties in differentiation
for adjoint method, a differentiable source term model was developed. To deal with a large
number of design variables, the gradient-based design optimization method using the
discrete adjoint approach was employed to minimize the distortion coefficient while
maintaining the baseline total pressure recovery ratio. As a validation of the proposed design
approach, optimization with three kinds of design parameters representing the effectiveness
of each vortex generator (a total of 33 design variables) was carried out with the original
source term model. The designed vortex generator configuration yields a substantial
improvement in inlet performance, which confirms the validity of the proposed design
approach. After the validation process, a complete design with five design parameters per
each vortex generator (a total of 55 design variables) was performed by using the
differentiable source term model. Through the complete design process, the performance of
target inlet was remarkably improved; the distortion coefficient was decreased over 79%
while maintaining the total pressure recovery ratio.
Language
English
URI
http://hdl.handle.net/10371/82441
DOI
https://doi.org/10.2514/6.2011-3535
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Others_기계항공공학부
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