陈诚, 陈其盛, 黄江涛, 聂胜阳, 张文琦, 焦瑾. 基于变弯度技术和协同射流的混合流动控制技术研究[J]. 工程力学, 2022, 39(11): 245-256. DOI: 10.6052/j.issn.1000-4750.2021.06.0479
引用本文: 陈诚, 陈其盛, 黄江涛, 聂胜阳, 张文琦, 焦瑾. 基于变弯度技术和协同射流的混合流动控制技术研究[J]. 工程力学, 2022, 39(11): 245-256. DOI: 10.6052/j.issn.1000-4750.2021.06.0479
CHEN Cheng, CHEN Qi-sheng, HUANG Jiang-tao, NIE Sheng-yang, ZHANG Wen-qi, JIAO Jin. HYBRID FLOW CONTROL TECHNOLOGY BASED ON VARIABLE CAMBER AND CO-FLOW JET[J]. Engineering Mechanics, 2022, 39(11): 245-256. DOI: 10.6052/j.issn.1000-4750.2021.06.0479
Citation: CHEN Cheng, CHEN Qi-sheng, HUANG Jiang-tao, NIE Sheng-yang, ZHANG Wen-qi, JIAO Jin. HYBRID FLOW CONTROL TECHNOLOGY BASED ON VARIABLE CAMBER AND CO-FLOW JET[J]. Engineering Mechanics, 2022, 39(11): 245-256. DOI: 10.6052/j.issn.1000-4750.2021.06.0479

基于变弯度技术和协同射流的混合流动控制技术研究

HYBRID FLOW CONTROL TECHNOLOGY BASED ON VARIABLE CAMBER AND CO-FLOW JET

  • 摘要: 现代飞机强调高速巡航特性且兼顾隐身特性,因此翼型往往采用厚度较小,前缘半径不大,弯度不大的薄翼型。这类翼型的低速气动性能较差,容易失速,限制了这类飞机的短距起降特性和载重能力,因此需要借助流动控制技术来改善低速特性。该文讨论新型的协同射流主动流动控制技术,同变弯度技术包括后缘变弯和前缘下垂技术等被动流动控制技术相结合,探索混合流动控制技术的流动控制机理和控制效果。基于数值模拟的结果发现:仅采用单一的流动控制技术在薄翼型上得到的控制效果有限,而将协同射流同变弯度技术结合的混合流动控制技术可同时发挥不同流动控制技术的优点(例如协同射流引起的后缘失速的推迟,下垂前缘带来的前缘失速推迟,后缘襟翼带来的零升迎角减小)。该文提供的混合流动控制方案可以将薄翼型的最大升力系数提升至CLmax=3.3127,相对原始构型提升了96%,具有广阔的工程应用前景。

     

    Abstract: Modern aircraft emphasizes the characteristics of high-speed cruise and stealth. As a result, the airfoil used usually has a relatively small thickness, a small leading edge radius and less camber. The performance of such airfoils is poor, with early flow stall at a low speed condition, and resulting in the limitation of the STOL characteristic and weight-carrying capacity of the aircraft. Thus, it is necessary to improve the aerodynamic performance of airfoil by using active flow control or passive flow control. In this paper, the innovative co-flow jet (CFJ) technology is investigated, which is coupled with variable camber technology (including the trailing-edge flap and leading-edge droop) and flow mechanism, as well as control efficiency of so-called hybrid flow control approach. As shown by numerical simulation results, a single flow control technology cannot improve the lift of the thin airfoil substantially. Nevertheless, the combination of CFJ with variable camber technology could realize the advantages of both technologies (e.g. the delay of trailing edge stall induced by CFJ, the delay of leading edge stall caused by droop nose, the decrease of zero-lift angle induced by trailing edge flap, etc.). The combination scheme of CFJ and variable camber technology in this paper could yield the maximum lift coefficient of CLmax=3.3127, 96% higher than that of the original airfoil, implying that the hybrid flow control technology has valuable potential for aviation industry application.

     

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