Flow-field measurements were obtained in the wake of a full-span Hybrid Wing Body model with internally blown flaps. The test was performed at the NASA Langley 14 x 22 Foot Subsonic Tunnel at low speeds. Off-body measurements were obtained with a 7-hole probe rake survey system. Three model configurations were investigated. At 0deg angle of attack the surveys were completed with 0deg and 60deg flap deflections. At 10deg angle of attack the wake surveys were completed with a slat and a 60deg flap deflection. The 7-hole probe results further quantified two known swirling regions (downstream of the outboard flap edge and the inboard/outboard flap juncture) for the 60deg flap cases with blowing. Flowfield results and the general trends are very similar for the two blowing cases at nozzle pressure ratios of 1.37 and 1.56. High downwash velocities correlated with the enhanced lift for the 60deg flap cases with blowing. Jet-induced effects are the largest at the most inboard station for all (three) velocity components due in part to the larger inboard slot height. The experimental data are being used to improve computational tools for high-lift wings with integrated powered-lift technologies.
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机译:流场测量是在带有内部吹动襟翼的全跨度混合翼机体模型中获得的。该测试在NASA Langley 14 x 22英尺亚音速隧道中以低速进行。使用7孔探针耙测量系统获得离体测量。研究了三种模型配置。在0度的迎角下,测量以0度和60度襟翼偏转完成。在攻角为10度时,尾迹测量是用板条和60度襟翼偏转完成的。 7孔探测结果进一步量化了60度襟翼吹动情况下两个已知的旋流区域(外侧襟翼边缘的下游和内侧/外侧襟翼的交界处)。在喷嘴压力比为1.37和1.56的两种吹气情况下,流场结果和总体趋势非常相似。高冲洗速度与60度襟翼吹气情况下提升的升力有关。在所有(三个)速度分量中,在最内侧站,喷射引起的影响最大,部分原因是内侧狭槽高度较大。实验数据被用于改进具有集成动力提升技术的高升力机翼的计算工具。
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