AM06-15-007 高揚力装置付き航空機風洞試験模型の空力特性(空気力学・高エンタルピー流(2),一般講演)

概要

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In this paper, the results of the wind tunnel testing for a high-lift configuration aircraft model in JAXA are given. The first testing of high-lift configuration model JSM was aiming to store large amount of basic aerodynamic information by various measurement techniques to provide the experimental data for CFD validation and to understand flow physics. Navier-Stokes computation was performed on unstructured hybrid mesh, simultaneously. As a result of the testing, two kinds of Reynolds number effects within linear region and also at stall region were observed. Analysis of static pressure distribution and flow visualization gave the knowledge to understand the aerodynamic performance. CFD could capture the whole characteristics in basic aerodynamics even for such a complicated model geometry and its flow field, while differences between the experimental results and CFD were shown.
2006-09-05