Stereoscopic PIV System Development for the JAXA 2m × 2m Transonic Wind Tunnel

Author

Kato, H. ; Watanabe, S. ; Hashimoto, T. ; Noguchi, M.

Author_Institution

Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji Higashi Chofu City, Tokyo 182-8522, JAPAN. Email Address: hirok@chofu.jaxa.jp

fYear

2005

fDate

Aug. 29 2005-Sept. 1 2005

Firstpage

308

Lastpage

312

Abstract

Stereoscopic PIV technique was applied to the JAXA next-generation supersonic transport (SST) jet experimental airplane model. The measurements have been performed in the JAXA 2m x 2m Transonic Wind tunnel. Application of PIV measurement techniques to transonic wind tunnels has particular difficulties associated with complex flows with shock waves. Due to these difficulties, practical experiments of PIV measurements in transonic wind tunnels are limited. In the present study, a fully remote-controlled stereoscopic PIV system is developed for velocity measurement of transonic complex flows, and preliminary results using the system are reported to evaluate the system capabilities. The tests were conducted at a freestream Mach number from 0.4 to 1.4. An example of raw PIV images captured by the camera around the flow-through nacelle intake. Location and shape of shock waves observed in the PIV results are in good agreement with schlieren results for identical test condition. The velocity field information of the PIV results is valuable in a precise validation of CFD.

Keywords

Aerospace engineering; Airplanes; Cameras; Cooling; Laser modes; Measurement techniques; Shock waves; Space technology; Testing; Velocity measurement;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation in Aerospace Simulation Facilities, 2005. iciasf '05. 21st International Congress on

Conference_Location

Sendai, Japan

Print_ISBN

0-7803-9096-2

Type

conf

DOI

10.1109/ICIASF.2005.1569937

Filename

1569937