Experimental investigation of isolated inlets for high agile missiles

Experimental studies are accomplished with two axially symmetric inlet models with different internal compressions. Main interest lies in covering a large and flexible maneuver range at supersonic speed. This requires an analysis of the performance such as pressure recovery and mass flow. lets are analyzed at the design Mach number M A = 3 in an angle of attack range of 0° ⩽ α ⩽ 30° in the Vertical Wind Tunnel (VMK) in Cologne. The tests indicate an operability up to α = 30 ° . Furthermore a loss of pressure recovery and mass flow is discovered at an angle of attack of α⩾18°. Accordingly boundary layer bleed is implemented to get a better pressure recovery and a delayed buzzing.