Natural laminar flow wing for supersonic conditions: Wind tunnel experiments, flight test and stability computations

被引：13

作者：

Vermeersch, Olivier ^{[1
]}

Yoshida, Kenji ^{[2
]}

Ueda, Yoshine ^{[2
]}

Arnal, Daniel ^{[1
]}

机构：

[1] Off Natl Etud & Rech Aerosp, French Aerosp Lab, Toulouse, France

[2] Japan Aerosp Explorat Agcy, Tokyo, Japan

来源：

PROGRESS IN AEROSPACE SCIENCES | 2015年 / 79卷

关键词：

Laminar/turbulent transition; Natural laminar flow; Supersonic; Tollmien-Schlichting waves; Cross-flow instabilities;

D O I：

10.1016/j.paerosci.2015.07.003

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

In the framework of next supersonic transport airplane generation, the Japan Aerospace exploration Agency (JAXA) has developed a new natural laminar flow highly swept wing. The design has been experimentally validated firstly in a supersonic wind tunnel and secondly accomplishing flight test. These experimental data were then analyzed and completed by numerical stability analyses in a joint research program between Onera and JAXA. At the design condition, for a Mach number M=2 at an altitude of h=18 km, results have confirmed the laminar design of the wing due to a strong attenuation of cross-flow instabilities ensuring an extended laminar zone. As the amplification of disturbances inside the boundary layer and transition process is very sensitive to external parameters, the impact of wall roughness of the models and the influence of Reynolds number on transition process have been carefully analyzed. (C) 2015 Elsevier Ltd. All rights reserved.

引用

页码：64 / 91

页数：28

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