Transition Analysis of Supersonic Natural Laminar Flow Wing at Flight Test Condition using PSE Approach

Author:

IDE Yuki,YOSHIDA Kenji,UEDA Yoshine

Publisher

Japan Society for Aeronautical and Space Sciences

Reference18 articles.

1. 1) Arnal, D.: Boundary Layer Transition Prediction Based on Linear Theory, AGARD/FDP-VKI Special Course on Progress in Transition Modeling, AGARD Report 793, 1994.

2. 2) Yoshida, K.: Supersonic Drag Reduction Technology on the Scaled Supersonic Experimental Airplane Project by JAXA, Progr. Aerospace Sci., 45 (2009), pp. 124-146.

3. 3) Yoshida, K., Sugiura, H., Ueda, Y., Ishikawa, H., Tokugawa, N., Atobe, T., Takagi, S., Arnal, D., Archambaud, J.-P. and Seraudie, A.: Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA Cooperative Research Project, JAXA-RR-08-007E, 2009.

4. 4) Yoshida, K., Ishida, Y., Noguchi, M., Ogoshi, H. and Inagaki, K.: Experimental and Numerical Analysis of Laminar Flow Control at Mach 1.4, AIAA Paper 99-3655, 1999.

5. 5) Ueda, Y., Yoshida, K., Matsushima, K. and Ishikawa, H.: Supersonic Natural-Laminar-Flow Wing-Design Concept at High-Reynolds-Number Conditions, AIAA J., 52 (2014), pp. 1294-1306.

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