To identify the source of severe aerodynamical vibration encountered with the complete airplane model support system of the NAL 2m x 2m Transonic Wind Tunnel at higher supersonic Mach numbers, static pressure distributions were measured on the surface of the model strut and the sidewall. The model strut is installed in the Semispan model Test Section which originally has a free space at the portion corresponding to the model support system position in the complete airplane model Test Section. Three model strut configurations were tested, and the effects of the sidewall streamwise divergence were observed by the divergence angle from the standard one sixth deg to one quarter deg and one third deg.
遷音速風洞における測定部模型支持装置周りの気流特性
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