Experimental investigation of isolated inlets for high agile missiles

Kurzfassung

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. The inlets are analyzed at the design Mach number MA = 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.