Application of PSP to 65-deg Delta Wing at Low Speeds
Recently, the pressure sensitive paint (PSP) technique is applied to measure the overall pressure distribution on a model surface. Pressure sensitive paint may be advantageous when compared to typical pressure taps and transducers but there are several error sources which are affected to accurate of PSP such as illumination of light source, temperature compensation, and model deformation. Especially, it is difficult to measure the small variation pressure at very low speeds. In this study, PSP technique is applied to a delta wing under the low speed to measure pressure field difference. Pressure is measured each different angle of attack in subsonic wind tunneL As a result, PSP pressure field is shown the difference caused by secondary vortex and vortex breakdown. Also, it is captured small pressure variation although there is occurred stall at high angle of attack. To prove the result measured pressure is compared with the result of the pressure tap and these values found closely approached with each other. The result is to show the possibility of PSP test under the M = 0.1. Therefore, it is visualized effectively using PSP at very low speeds.
Pressure Sensitive Paint(PSP) pressure measurement system wind tunnel test low speed delta wing
Jeong Hui Seo Dongsu Byun Yunghwan Lee Jaewoo Kim Sangho
Department of Aerospace System Engineering, Konkuk University, Seoul 143701, South Korea Department of Aerospace System Engineering, Konkuk University, Seoul 143701,South Korea
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
211-214
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）