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Model and Boundary Aerodynamic Data from High Blockage Two-Dimensional Airfoil Tests in a Shallow Unstreamlined Transonic Flexible Walled Test Section.

机译:浅层无流线型跨音速柔性围护结构试验中高阻塞二维翼型试验的模型和边界气动数据。

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摘要

Data for a NACA 0012-64 airfoil at Mach numbers of 0.3, 0.5, and 0.7 with the test section flexible walls set in the 'straight' position are presented because they may prove useful in the development of wind tunnel correction techniques.

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