Experimental Investigation of Leading Edge Bluntness Effects on Hypersonic Tow-dimensional Inlet

AbstractThe leading edge bluntness effects on inlet boundary layer transition had been studied based on a typical hypersonic two-dimensional inlet. Four leading edge radii(R=0.05mm, R =0.1mm, R =0.2mm, R =0.25mm) had been experimented in FD-07 wind tunnel, including natural transition and artificial transition. The location of boundary layer transition was identified through the corner pressure distribution characteristics and inlet starting, by this method, we had obtained the regular of boundary layer transition location with the leading edge radii. Experimental results showed that, under the wind tunnel condition, the boundary layer transition location moved down stream with increasing the leading edge radius. The inlet would not start for leading edge radius R = 0.25mm and we had designed artificial transition strip based onlinear stability theory(LST) to make the inlet start successfully