航空学报 > 2023, Vol. 44 Issue (6): 127215-127215   doi: 10.7527/S1000-6893.2022.27215

机体尾缘形状对高压捕获翼构型亚声速特性影响

王浩祥1,2, 肖尧1,2(), 张凯凯1,2, 李广利1,2, 常思源1, 田中伟3, 崔凯1,2   

  1. 1.中国科学院 力学研究所 高温气动国家重点实验室,北京 100190
    2.中国科学院大学 工程科学学院,北京 100049
    3.中国科学院 力学研究所,北京 100190
  • 收稿日期:2022-03-29 修回日期:2022-04-26 接受日期:2022-05-16 出版日期:2023-03-25 发布日期:2022-05-19
  • 通讯作者: 肖尧 E-mail:xiaoyao@imech.ac.cn
  • 基金资助:
    国家自然科学基金(12002347);中国科学院基础前沿科学研究计划(ZDBS-LY-JSC005)

Effect of body trailing edge shape on subsonic flow characteristics of high-pressure capturing wing configuration

Haoxiang WANG1,2, Yao XIAO1,2(), Kaikai ZHANG1,2, Guangli LI1,2, Siyuan CHANG1, Zhongwei TIAN3, Kai CUI1,2   

  1. 1.State Key Laboratory of High-Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China
    2.School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China
    3.Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China
  • Received:2022-03-29 Revised:2022-04-26 Accepted:2022-05-16 Online:2023-03-25 Published:2022-05-19
  • Contact: Yao XIAO E-mail:xiaoyao@imech.ac.cn
  • Supported by:
    National Natural Science Foundation of China(12002347);Basic Frontier Science Research Program of Chinese Academy of Sciences(ZDBS-LY-JSC005)

摘要:

基于圆锥-圆台组合平板捕获翼构型,通过改变尾缘展向扩张角,获得一系列不同外形,在典型亚声速(Ma=0.5)来流条件下开展数值计算,并重点分析了机体尾部截面形状和攻角变化对流动特性和气动特性的影响。结果表明:在0°攻角状态下,机体尾截面展向变宽,机体与捕获翼之间的流场区域对来流的扩张减弱,机体圆台上表面的逆压梯度减小,可有效抑制机-翼之间流场内的流动分离现象,同时整机升力系数增大,阻力系数先减小后增大。随攻角增大,机体圆台上表面压力增大,分离区范围逐渐缩小直至消失,机体尾截面展向变宽可加速分离区消失的进程。当攻角进一步增大时,机体背风面出现横向绕流,但机体尾截面展向变宽可以延缓横向绕流的发展。计算结果还表明,随攻角增大整机升力及阻力主要由捕获翼贡献,机体贡献的气动力随攻角变化不敏感,机体尾截面展向变宽对整机焦点位置影响较小。机体下表面几何形状变化对机体与捕获翼之间的区域内流动特性和捕获翼部件的气动力特性无明显影响。

关键词: 高压捕获翼, 亚声速, 流动特性, 流动分离, 尾缘

Abstract:

Based on the conceptual configuration combining the conical-cone airframe and flat plate capturing wing configuration, a series of different shapes were obtained by changing the side expansion angle of the trailing edge. The configuration was solved by computational fluid dynamics under the condition of typical subsonic flow (Ma=0.5). The results show that, at the angle of attack of 0°, the spanwise section of the body tail widened, the expansion effect of the channel between the body and the capturing wing on the incoming flow was weakened, and the reverse pressure gradient on the upper surface of the body platform was reduced, which could effectively inhibit the flow separation phenomenon in the channel. In addition, the whole vehicle lift coefficient rose, and the drag coefficient first fell and then grew. With the increase of the angle of attack, the pressure on the upper surface of the round platform of the body climbed, while the range of the separation zone gradually declined until it disappeared. Furthermore, the spanwise widening of the tail section of the body could accelerate the disappearance of the separation zone. When the angle of attack increased further, the transverse flow appeared on the leeward side of the body, while the spanwise widening of the body tail section could delay the development of the transverse flow. As the angle of attack increased, the calculation results also show that the lift and drag of the whole machine were mainly attributed to the capturing wing. The aerodynamic force contributed by the body was not sensitive to the change of the angle of attack. The spanwise widening of the body tail section had little effect on the aerodynamic center of the whole vehicle. The geometry change of the lower surface of the body had no significant effect on the flow characteristics in the channel between the body and the capturing wing and the aerodynamic characteristics of the capturing wing.

Key words: high-pressure capturing wing, subsonic, flow characteristics, flow separation, trailing edge

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