Unsteady Transonic Flow over a Transport-Type Swept Wing

被引:28
|
作者
Steimle, P. Christian [1 ]
Karhoff, Daniel-Christian [2 ]
Schroeder, Wolfgang [2 ]
机构
[1] Eurockot Launch Serv GmbH, D-28361 Bremen, Germany
[2] Rhein Westfal TH Aachen, Inst Aerodynam, D-52062 Aachen, Germany
关键词
PRESSURE-SENSITIVE PAINT; ANODIC POROUS ALUMINA; BUFFET; OSCILLATIONS; FLUTTER; PSP;
D O I
10.2514/1.J051187
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The unsteady transonic flow around a flexible transport-type swept-wing configuration with the supercritical airfoil BAC 3-11/RES/30/21 is studied regarding the effects of dynamic shock/boundary-layer interaction involving separated-flow areas on the local fluid-structure coupling at unit Reynolds numbers of around 1.5 x 10(7) m(-1). A fast-responding pressure-sensitive-paint system using pyrene on anodic aluminum binder is applied to measure the unsteady pressure distribution on the entire wing surface, with high spatial and temporal resolution providing a unique view on the spanwise flow development and self-induced shock oscillations. The aeroelastic response of the wing structure is synchronously recorded by videogrammetric deformation measurement. Flow cases with incipient separation and full-scale separation at Mach numbers of 0.86 and 0.92 are compared. A weak shock/boundary-layer interaction with incipient separation has minor effects on the wing structure, despite the occurrence of large pressure fluctuations, whereas the strong interaction involving shock-induced separation results not only in significantly weaker fluctuations in the pressure field, but also in a strong fluid-structure coupling.
引用
收藏
页码:399 / 415
页数:17
相关论文
共 50 条