环量控制技术研究

发布时间：2018-12-21 18:38

【摘要】：未来军/民运输机的高性能要求促使近年来环量控制技术正成为研究的新热点。本文简单介绍了环量控制研究的进展;深入讨论了包括二维环量控制翼型标模和CCA/OTW(Circulation Control Airfoil/Over the Wing)实验、半模型子系统实验和三维翼身融合体全机实验等可供CFD验证用的NASA实验研究。在2个尺寸相近的风洞中对同一二维标模的实验结果表明,源于切向吹气的最大升力系数CLmax在中等缝道出口高度时可达8~9。数据对比表明此实验结果可供计算流体力学(CFD)验证用。二维CCA/OTW实验表明,发动机位置前移可大幅增大失速迎角和CLmax;CCA后缘吹气噪声的低频部分强度与速度的8次方成正比,高频部分与速度的6次方成正比。半模型子系统的FACT-MAC跨声速实验不仅可研究高雷诺数效应,且可提供2种飞行状态的数据。初步结果表明,与无射流的低速数据相比,在α=25°时CL增大约33%,跨声速时在非设计状态下射流可有效地使激波诱导的分离再附,在保持原有强度下激波位置可后推5%的弦长。三维全机CCW/OTW的实验数据尚在整理分析中,但初步结果已表明,应用前缘吹气可将失速迎角增大至25°,CLmax增大至6,正确安排OTW位置可增大升力线斜率等。
[Abstract]:In recent years, the high performance requirement of military / civilian transport aircraft is becoming a new research hotspot. In this paper, the research progress of loop control is briefly introduced. In this paper, the experimental research of NASA which can be used for CFD verification is discussed in detail, including 2-D loop control airfoil scalar model and CCA/OTW (Circulation Control Airfoil/Over the Wing) experiment, semi-model subsystem experiment and three-dimension pterygoid fusion whole aircraft experiment. The experimental results of the same two-dimensional model in two similar wind tunnels show that the maximum lift coefficient (CLmax) derived from tangential blowing can reach 8 / 9 at the outlet height of the middle seams. Data comparison shows that the experimental results can be used for (CFD) verification of computational fluid dynamics. Two-dimensional CCA/OTW experiments show that the forward displacement of engine position can greatly increase the intensity of the low-frequency part of the stall angle of attack and the CLmax;CCA rear edge blowing noise, and the intensity of the low-frequency part is proportional to the eighth power of the velocity, and the high-frequency part is directly proportional to the sixth power of the velocity. The FACT-MAC transonic experiments of the semi-model subsystem can not only study the high Reynolds number effect, but also provide the data of two flight states. The preliminary results show that compared with the low speed data without jet, the CL increases about 33% at 伪 = 25 掳, and the jet can effectively reattach shock induced separation at transonic velocity in a non-designed state. The shock wave position can be pushed back by 5% chord length under the original strength. The experimental data of 3D CCW/OTW are still in the process of analysis, but the preliminary results show that the stall angle of attack can be increased to 25 掳, the CLmax can be increased to 6, and the slope of lift line can be increased by correctly arranging the position of OTW.
【作者单位】：北京航空航天大学航空科学与工程学院;
【分类号】：V211.41

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