Inverse design of supersonic airfoils using integral equations

Shinkyu Jeong; Kisa Matsushima; Toshiyuki Iwamiya; Shigeru Obayashi; Kazuhiro Nakahashi

doi:10.2514/2.2478

Inverse design of supersonic airfoils using integral equations

Shinkyu Jeong, Kisa Matsushima, Toshiyuki Iwamiya, Shigeru Obayashi, Kazuhiro Nakahashi

IFS - Creative Flow Research Division

Research output: Contribution to journal › Article › peer-review

1 Citation (Scopus)

Abstract

Takanashi's inverse design method is extended to supersonic airfoil design. The validity of the extended method is confirmed through numerical calculations using NACA 1204 and NACA 0003 as reference airfoils. Numerical results show that the present inverse code can be used to change not only geometrics but also the angle of attack of airfoils.

Original language	English
Pages (from-to)	606-608
Number of pages	3
Journal	Journal of Aircraft
Volume	36
Issue number	3
DOIs	https://doi.org/10.2514/2.2478
Publication status	Published - 1999

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10.2514/2.2478

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title = "Inverse design of supersonic airfoils using integral equations",

abstract = "Takanashi's inverse design method is extended to supersonic airfoil design. The validity of the extended method is confirmed through numerical calculations using NACA 1204 and NACA 0003 as reference airfoils. Numerical results show that the present inverse code can be used to change not only geometrics but also the angle of attack of airfoils.",

author = "Shinkyu Jeong and Kisa Matsushima and Toshiyuki Iwamiya and Shigeru Obayashi and Kazuhiro Nakahashi",

year = "1999",

doi = "10.2514/2.2478",

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journal = "Journal of Aircraft",

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publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

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T1 - Inverse design of supersonic airfoils using integral equations

AU - Jeong, Shinkyu

AU - Matsushima, Kisa

AU - Iwamiya, Toshiyuki

AU - Obayashi, Shigeru

AU - Nakahashi, Kazuhiro

PY - 1999

Y1 - 1999

N2 - Takanashi's inverse design method is extended to supersonic airfoil design. The validity of the extended method is confirmed through numerical calculations using NACA 1204 and NACA 0003 as reference airfoils. Numerical results show that the present inverse code can be used to change not only geometrics but also the angle of attack of airfoils.

AB - Takanashi's inverse design method is extended to supersonic airfoil design. The validity of the extended method is confirmed through numerical calculations using NACA 1204 and NACA 0003 as reference airfoils. Numerical results show that the present inverse code can be used to change not only geometrics but also the angle of attack of airfoils.

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JO - Journal of Aircraft

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ER -

Inverse design of supersonic airfoils using integral equations

Abstract

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