螺旋桨前掠翼模型气动特性数值模拟  

Numerical Simulation of Aerodynamic Characteristics of a Forward Swept Wing Model with Propeller

作　　者：马震宇 程雪枫 董向阳 姚希双 MA Zhenyu;CHENG Xuefeng;DONG Xiangyang;YAO Xisuang(School of Aeronautical Engineering,Zhengzhou University of Aeronautics,Zhengzhou 450046,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;AVIC Huiyang Aviation Propeller Co.,Ltd.,Baoding 071051,China)

机构地区：[1]郑州航空工业管理学院航空工程学院,河南郑州450046 [2]西北工业大学动力与能源学院,陕西西安710072 [3]中航工业惠阳航空螺旋桨有限责任公司,河北保定071051

出　　处：《机械》2020年第2期19-24,共6页Machinery

基　　金：河南省高等学校重点科研项目计划(16A590001);郑州航院教育科学研究基金项目(ZHJY18-11)。

摘　　要：前掠翼与串置翼各自具有独特的气动和结构优势,螺旋桨滑流对其的气动影响作用需要分析研究。基于一种螺旋桨动力串置前掠翼布局模型,螺旋桨直径0.232 m,应用UG和ICEM CFD软件,划分大小流动区域并考虑壁面粘性附面层特点,构建三维模型的结构/非结构混合网格模型。应用FLUENT软件,对无螺旋桨时模型的低速纵向气动力进行数值模拟,在飞行马赫数0.3和5°攻角时模型升阻比获得最大为7。在最大升阻比状态下,考虑前置螺旋桨工作的影响,数值模拟螺旋桨滑流作用下模型的低速气动力特性,螺旋桨转速24638 r/min,发现旋转滑流对前后翼都有降低绕流逆压梯度作用,前翼和后翼压差载荷均有所增大,模型总体升力相应提高。The forward swept wing and the tandem wing have their unique aerodynamic and structural advantages,and the aerodynamic influence of the propeller slipstream needs to be analyzed.On the basis of a tandem forward swept wing model powered by propeller with a diameter of 0.232m,UG and ICEM CFD software are used to divide the flow area and discover the characteristics of the adhesive wall boundary layer to construct a 3D model and structure/unstructured hybrid mesh model.And then,the low-speed longitudinal aerodynamics of the model without propeller is numerically simulated though FLUENT software,.The maximal lift-to-drag ratio of the model is obtained at the flight of Mach 0.3 and angle of attack 5°.Under the condition of maximum lift-to-drag ratio,the low-speed aerodynamic characteristics of the model influenced by propeller slip flow are numerically simulated while the front propeller is working,and the rotation speed of the propeller is 24,638 r/min.It is found that the slipstream has the effect of reducing counter-pressure gradient of the flow around the front and the rear wings;the overall lift of the model increases with the increase of the differential pressure load on the front and the rear wings.

关 键 词：前掠翼布局模型 串置式 螺旋桨滑流 气动特性 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.4