高超声速进气道边界层强制转捩试验

Test of forced boundary-layer transition on hypersonic inlet

在FL-31高超声速风洞分别开展了进气道的自然转捩和强制转捩风洞试验,试验Ma数为5、6和7,迎角为1°。通过红外热图得到了壁面的热流分布,从中得到了转捩区域。强制转捩装置为钻石型涡流发生器。随着涡流发生器高度的增加,强制转捩区域逐渐前移,得到了涡流发生器的有效高度,实现了强制转捩的目的。

The experment of natural transition and forced-transition has been carried out in FL-31 hypersonic wind tunnel for inlet model with Mach numbers 5,6,7 and one degree of angle of attack.The heat-transfer distributions are measured through infrared thermograph,from which the transition region can be obtained.The forced-transition equipment is a kind of vortex generator in diamond shape.With increasing height of vortex generator（trip）,the forced-transition region moves forward.At last,the effective height of vortex generator is obtained.The experiment succeeds in achieving forced-transition.