高超声速双模块内转式进气道的流动特性研究-Part II 攻角影响

Flowfield of Hypersonic Bimodule Inward-Turning Inlet- Part II Effects of Attack Angle

关键词:  双模块进气道  内转式进气道  攻角特性  激波  试验研究

Key words:  Bimodule inlet  Inward turning inlet  Attack angle characteristics  Shock wave  Experimental investigation

摘要:

为了研究飞行攻角对高超声速双模块内转式进气道流动的影响，通过试验和仿真方法，获得了0°，4°和6°攻角条件下进气道模块内的流动结构。结果表明：在本文研究的攻角范围内，进气道均可起动，进气道压缩面侧的压力变化体现了基准流场的流动特性。在耦合作用下进气道模块间压缩面诱导的激波形态沿流向由弓形逐渐发展为钟形，并且在外压缩激波的扫掠影响下进气道的三个角区出现了强度不同的旋涡结构。进气道压缩面侧的角区旋涡随着攻角的增大而逐渐增强，而进气道出口截面上低能流区域随着攻角的增大而逐渐减小。低能流区域内的二次旋涡呈现不同的变化趋势，位于上半截面的旋涡随着攻角的增大逐渐向上移动，而位于下半截面的旋涡位置基本保持不变。

Abstract:

In order to study the effects of the inlet attack angle on the flow in hypersonic bimodule inward-turning inlet， the experimental and numerical research were carried out to obtain the flow structures of the inlet at three different attack angles of 0°，4°and 6°. The results show that the inlet is in the started state within the range of the attack angle， and the pressure variation on the compression surface of the inlet reflects the characteristics of the basic flowfield. Under the coupling action， the compression shock wave induced by the compression surface between the inlet modules gradually develops from bow shape to bell shape along the flow direction， and the vortex structures with different intensities appear in the three corner regions of the inlet under the influence of the sweep of the compression shock wave. With the increase of the attack angle， the vortex in the corner area on the upper side of the inlet compression surface gradually increases， while the low-energy flow area in the outlet section of the inlet gradually decreases. However， the secondary vortices in the low-energy flow region show different changing trends. The vortices in the upper half section gradually move upward with the increase of the attack angle， while the position of the vortexes in the lower half remains basically unchanged.