摘要
针对类HTV-2控制翼诱导的局部层流分离开展了研究工作。结合实验结果,数值模拟了类HTV-2控制翼诱导的层流分离流动特性,发现其分离形态呈扁长尖形,分离区内存在一对反向对称旋涡,此类分离与矩形平板/三维楔诱导分离形式不同,前体形状对控制翼诱导层流分离具有重要影响。研究了类HTV-2控制翼诱导分离随偏转角的变化规律,受前体横流效应影响,控制翼前物面流动从两侧向中间聚拢,翼前逆压梯度增大,即使在5°小偏转角仍诱导分离,该现象与实验相符,较以往对典型矩形平板/三维楔层流分离初始分离角的认识不同。
Characteristics of hypersonic laminar separation induced by the control surface of a HTV-2 like configuration were investigated numerically.It is found that the patterns of the separations induced by the control surface have long flat shape and a pair of counter rotating vortices.These patterns are very different from those induced by a rectangle plane/3 D wedge.A detailed analysis was carried out to explain this behavior.Studies were also conducted to examine the effects of the flap deflection on laminar separation.Interestingly,since the influence of the forebody shape of the HTV-2 like configuration,the flow gathers from both sides to the middle and pressure gradient boosts before the control surface.A separated flow is still induced because of the control surface,even at the angle of deflection as small as 5°.This phenomenon is in a good agreement with the experimental result,and is different from the generally understanding about initial separation angle of compression corner.
作者
陈政
倪招勇
王军旗
CHEN Zheng , NI Zhaoyong, WANG Junqi(China Academy of Aerospace Aerodynamics, Beijing 100074, Chin)
出处
《空气动力学学报》
CSCD
北大核心
2018年第3期514-517,共4页
Acta Aerodynamica Sinica
关键词
高超声速
控制翼
层流分离
前体影响
数值模拟
hypersonic flow
control surface
laminar separation
forebody effect
numericalinvestigation
