| Bildiri Türü | Tebliğ/Bildiri | Bildiri Dili | İngilizce |
| Bildiri Alt Türü | Tam Metin Olarak Yayınlanan Tebliğ (Uluslararası Kongre/Sempozyum) | ||
| Bildiri Niteliği | Alanında Hakemli Uluslararası Kongre/Sempozyum | ||
| Kongre Adı | 5th International Conference on Engineering and Natural Sciences | ||
| Kongre Tarihi | 12-06-2019 / 16-06-2019 | ||
| Basıldığı Ülke | Çek Cumhuriyeti | Basıldığı Şehir | Prag |
| UAK Araştırma Alanları |
Aerodinamik
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| Özet |
| In this study, it is studied to improve the vortex due to flow separation over the wing upper surface caused by pressure difference between the wing surfaces based on wing profile structure in the straight flight of an UAVs by using active blowing method. It is investigated to obtain the best efficiency from the compressed air blown into the flow. For this reason, the output angle of the air blown according to the flow is changed and the optimum blowing angle is decided. The position, area and pressure outlet magnitude of the air used for active blowing over the wing upper surface are kept constant. On the contrary, only the outlet angle of the compressed air is changed according to the top surface of the wing. The analyses are performed for the negative and positive different angles of attack of the UAVs. Thus, the effect of the blowing angle which is used as a variable on the performance has been tried to be evaluated. It is observed that the increase of the blowing angle causes a reverse flow on the wing after a certain size. In addition to this, this study shows that the change in the blowing angle alone does not cause much change in the performance of the UAVs, which has a low pressure outlet value. |
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