Experimental investigations are performed to determine the effect of the passive porous coating on the stability of the hypersonic boundary layer on the cone at small angles of attack. Measurements of the pressure disturbances on the cone surface showed that, the increase of the angle of attack leads to decrease of the second-mode amplitude, when the smooth cone side is the windward side. On the leeward side the amplitude of the disturbances increase with the angle of attack until the boundary layer is laminar. It was found that the ultrasonically absorptive coating leads to the energy decrease of the second-mode disturbances on both leeward and windward side of the sharp cone.
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