Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed : JAXA-ONERA cooperative research project

• Published in: 宇宙航空研究開発機構研究開発報告 Vol. 8; pp. 1 - 104
• Main Authors: YOSHIDA Kenji, SUGIURA Hiroki, UEDA Yoshine, ISHIKAWA Hiroaki, TOKUGAWA Naoko, ATOBE Takashi, TAKAGI Shohei, ARNAL Daniel, ARCHAMBAUD Jean-Pierre, SERAUDIE Alain
• Format: Journal Article
• Language: English
• Published: 宇宙航空研究開発機構 01.03.2009; Japan Aerospace Exploration Agency
• Subjects: boundary layer transition; eN method; linear stability analysis; natural laminar flow; supersonic flow; transition measurement
• ISSN: 1349-1113

In the aerodynamic design of the National EXperimental Supersonic Transport (NEXST) program, a supersonic natural laminar flow (NLF) wing design concept was originally developed. Before the flight test of the NEXST-1 airplane, more detailed transition analysis should be performed in order to validate the NLF wing effect. Therefore, the JAXA-ONERA cooperative research project started in April 2000, because ONERA had great ability of analyzing transition phenomena and JAXA had some experimental transition data in supersonic flow. In the transition analysis on the sharp cone with a half angle of 5 degrees, the nose cone, and the NLF wing of the NEXST-1 airplane, good cross validation of both ONERA's and JAXA 's eN codes was obtained. There was also high correlation between the experimental results in ONERA's continuous circuit-flow type supersonic wind tunnel and both laboratories' predictions under the assumption of a critical transition N value of 6. In addition, a risk of transition due to attachment-line contamination was predicted at inner wing, using the well-known Poll's criterion.