| abstract |
A control system for suppression of shock-induced flow separation caused by the interaction of turbulent boundary layer air and a strong normal shock in the air inlet of a supersonic aircraft by application of continuous bleeding upstream and across the shock boundary layer interaction region of the inlet through a porous cover which leads to a row of plenums from whence the bleed air is exhausted to atmosphere, through a controlled incrementally operated door. The control system can control interactions with normal shock strength approaching Mach=2 in strength. |