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Amirreza Shahsavari(아미레자 샤사바리),Mahdi Nili-Ahmadabadi(마흐디 닐리-아마다바디),Kyung Chun Kim(김경천) 대한기계학회 2020 대한기계학회 춘추학술대회 Vol.2020 No.12
The present study attempts to improve the aerodynamic performance of a slender delta wing. In this study, the effect of needle vortex generators on the flow of a delta wing with a sweep angle of 65° was studied. The experiments were performed at AOA= 20 degrees at a speed of 2.6 m/s on two delta wings with and without equipped needle vortex generators at the leading edge and a Reynolds number of Re = 2.6 × 10⁴. Smoke and laser flow visualization were used to understand the effect of the vortex generator on the flow over the delta wing at six different sections of the delta wing. The results showed that the use of the needle vortex generators along the leading edge of the delta wing makes the vortices smaller and closer to the wing surface. The needle vortex generators on the leading edge also cause the vortex breakdown to postpone.