| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2016: ¥650,000 (Direct Cost: ¥500,000、Indirect Cost: ¥150,000)
Fiscal Year 2015: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
Fiscal Year 2014: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
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| Outline of Final Research Achievements |
In this study, the advance aerodynamic measurement techniques which were a balance system, a wake measurement technique and a focusing schlieren PIV technique were considered for the establishment of the aerodynamic forces measurement and flow visualizations in the cryogenic wind tunnel. As a results, the simple correction technique of the cryogenic balance system was established for the small cryogenic wind tunnel. And the balance system can measure the aerodynamic forces by this technique. The effect of the wing tip plate of the supersonic biplane became clear by the wake measurement. Moreover the source grid of the lattice type in the focusing schlieren PIV technique that was proposed in the study can measure the flow velocity quantitatively.
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