航空学报 > 2023, Vol. 44 Issue (8): 127349-127349   doi: 10.7527/S1000-6893.2022.27349

翼反角对高压捕获翼构型高超气动特性的影响

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

  1. 1.中国科学院 力学研究所 高温气体动力学国家重点实验室,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 宽域飞行工程科学与应用中心,北京 100190
  • 收稿日期:2022-04-29 修回日期:2022-07-29 接受日期:2022-08-25 出版日期:2023-04-25 发布日期:2022-08-31
  • 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 wing dihedral and anhedral angles on hypersonic aerodynamic characteristics of high-pressure capturing wing configuration

Siyuan CHANG1, Yao XIAO1,2(), Guangli LI1,2, Zhongwei TIAN3, Kaikai ZHANG1,2, 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.Wide Field Flight Engineering Science and Application Center,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China
  • Received:2022-04-29 Revised:2022-07-29 Accepted:2022-08-25 Online:2023-04-25 Published:2022-08-31
  • 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:

为研究翼反角变化对高压捕获翼构型高超声速气动特性的影响,基于一种双翼面、单支撑、翼身组合布局的高压捕获翼概念构型,以飞行马赫数6,飞行高度30 km为计算状态,捕获翼和机体三角翼上/下反角为设计变量,结合均匀试验设计方法、数值模拟方法和Kriging建模方法,探寻了升阻特性、纵向和横航向稳定性随翼反角的变化规律。结果表明,升力、阻力及升阻比随翼反角的变化规律基本一致,且对上反角变化更加敏感;小攻角时,翼面上反会明显降低升阻比,而下反会使升阻比先略微增大后缓慢减小;大攻角时,翼反角对升阻比的影响较小;纵向稳定性主要受三角翼反角的影响,三角翼上反时,纵向稳定性降低,下反时,纵向稳定性基本不变;翼面上/下反都会提高航向稳定性,但下反的效果更明显;翼面上反会提高横向稳定性,下反则降低,但大攻角飞行时,三角翼上反角过大可能会导致横向稳定性降低。

关键词: 高压捕获翼, 高超声速, 气动特性, 上/下反角, 稳定性

Abstract:

To study the influence of wing dihedral/anhedral angle changes on the hypersonic aerodynamic characteristics of the High-pressure Capturing Wing (HCW) configuration, we studied the variation law of the lift-drag characteristics, and longitudinal and lateral-directional stability with the change of wing dihedral/anhedral angles based on a HCW concept configuration under the computation conditions of Mach number 6 and an altitude of 30 km. The design variables are dihedral/anhedral angles of HCW and delta wings, and some techniques, such as the uniform experimental design method, numerical simulation method, and Kriging modeling method, were utilized in the analysis. The results show that the lift, drag, and lift-drag ratio have similar variation trends with the change of wing dihedral/anhedral angles, and are more sensitive to the change of the dihedral angle. At small angles of attack, the wing dihedral significantly reduces the lift-drag ratio, while the anhedral slightly increases and then slowly decreases it. At large angles of attack, the wing dihedral/anhedral angles have less influence on the lift-drag ratio. The longitudinal stability is mainly affected by the dihedral/anhedral angles of the delta wing. Specifically, the delta wing dihedral decreases the longitudinal stability, while the anhedral hardly affects it. Both the wing dihedral and anhedral angles improve the directional stability, with the effect of the anhedral stronger. The wing dihedral raises the lateral stability, while the anhedral lowers it. However, at a large angle of attack, the large dihedral angle of the delta wing may lead to a decrease in lateral stability.

Key words: High-pressure Capturing Wing (HCW), hypersonic, aerodynamic characteristics, dihedral/anhedral angles, stability

中图分类号: