Experiment study on supersonic inlet in dual-model scramjet

Two types of three dimensional sidewall compression inlet models with 6° sidewall angle,45° swept angle and isolator were designed and experimentally investigated.The models were specially designed in 4° and 8° ramp angle.The Mach numbers of wind turnal were 5.3 and 3.85.The experimental results indicated that mass flow rate and total pressure recovery are higher in the condition of higher Mach number and lower ramp angle.Static pressure ratio in model remains constant in the condition of different ramp angles.