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翼反角对高压捕获翼构型亚声速气动特性影响分析研究

EFFECT OF WING DIHEDRAL AND ANHEDRAL ANGLES ON SUBSONIC AERODYNAMIC CHARACTERISTICS OF HCW CONFIGURATION

  • 摘要: 高压捕获翼新型气动布局在高超声速设计状态下具有较好的气动性能, 新升力面的引入使其在亚声速条件下也具有较大的升力, 但在亚声速下的稳定特性还有待研究. 基于高压捕获翼气动布局基本原理, 在机身-三角翼组合体上添加单支撑和捕获翼, 设计了一种参数化高压捕获翼概念构型. 以捕获翼和机体三角翼上/下反角为设计变量, 采用均匀试验设计、计算流体力学数值计算方法及Kriging代理模型方法, 研究了0° ~ 10°攻角状态下不同翼反角对高压捕获翼构型亚声速气动特性的影响, 重点分析了升阻特性、纵向和横航向稳定性的变化规律以及流场涡结构等. 结果表明, 小攻角状态下翼反角对升阻比的影响比大攻角更加显著, 捕获翼上反时, 升阻比略微增大, 下反则升阻比减小; 三角翼上反时, 升阻比减小, 下反则升阻比先略微增大后缓慢减小; 翼反角对纵向稳定性的总体影响较小, 捕获翼上反会稍微提高纵向稳定性, 而三角翼上反则会降低纵向稳定性; 捕获翼或三角翼上反都会增强横向稳定性, 下反则减弱横向稳定性, 但大攻角状态时, 三角翼上反角过大对提升横向稳定性作用有限; 捕获翼上反航向稳定性增强, 下反航向稳定性则减弱, 而三角翼下反对提升航向稳定性的整体效果比上反更加显著.

     

    Abstract: High-pressure capturing wing (HCW) novel aerodynamic layout has good aerodynamic performance in the hypersonic design state, and the import of the new lift wing provides more lift for it under subsonic conditions, but its aerodynamic stability characteristics at subsonic speed have yet to be studied further. In this paper, a parametric HCW concept configuration was presented based on the basic design principle of HCW aerodynamic layout, by adding an HCW with single support to a delta wing-body combination. The influence of wing dihedral/anhedral angle variations on subsonic aerodynamic characteristics of HCW configuration at the angle of attack (AOA) range of 0° to 10° was studied by utilizing uniform experimental design, computational fluid dynamics numerical simulation, and Kriging surrogate model, which regarded the dihedral/anhedral angles of both HCW and delta wing as the design variables. Specifically, the variation law of lift-drag characteristics, longitudinal and lateral-directional stability characteristics, and flow field vortex structures were analyzed. The results show that the influence of wing dihedral/anhedral angles on the lift-drag ratio (L/D) at low AOA is more significant than that at high AOA. The increase in HCW dihedral angle improves L/D of configuration, while the increase in HCW anhedral angle or delta wing dihedral angle reduces L/D. As the delta wing anhedral is increased from 0°, L/D has a slight improvement initially and then slowly reduces. The longitudinal stability, which is generally less affected by wing dihedral/anhedral angles, slightly improves as the HCW dihedral angle increases but reduces as the delta wing dihedral angle increases. Moreover, the lateral stability improves as the HCW or delta wing dihedral angle increases but reduces as the anhedral angle increases. However, at the high angle of attack, the improvement of lateral stability may be limited while the delta wing has a large anhedral angle. As for the directional stability, the increase in HCW dihedral angle improves it, while HCW anhedral angle reduces it. In particular, the increase in both the dihedral and anhedral angles of the delta wing can improve the directional stability, but the effect of the anhedral angle is stronger.

     

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