An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility

Abstract

The performance of three chin-intakes for airbreathing missiles with high agility has been investigated in a large maneuver range at supersonic speed. This experimental study is recovery and mass flow were discovered at angles of attack greater than 18°. To understand these effects in more details chin-intakes have been analyzed at a design Mach number of 3.0 at angles of attack ranging from -30° to 30° and at angles of sideslip ranging from -30° and 30° in the Trisonic Wind Tunnel. The results clearly show that boundary layer flow, vortices and flow sepration are responsible for the losses of pressure recovery and mass flow. The subsequently added boundary layer bleed permits a better pressure recovery and a delay of the intake buzzing.