Aerodynamic Layout Optimization Of The Device In Supersonic Free Jet Simulated Altitude Test

Aero-engine is the heart of the aircraft, it's techniques of test must be developed as the same step as it's performance. Nowadays, the Free-jet Simulated Altitude Test has dominated in the Aero-engine Simulated Altitude Tests, which include another two types: Directconnected Wind Tunnel and Aero-propelled Wind Tunnel. So, it has profound significance of China's aero-engine development to research on the techniques of the Free-jet Simulated Altitude Test.Theoretical research of supersonic free-jet flow mechanism, design binary supersonic nozzle by characteristic-line method to numerical simulate with different expansion conditions, conclude the derivation relationship which between the boundary of potential core region and supersonic geometry that for the purpose of establishing the potential core region equation.Design the wedge plate external pressure supersonic inlet and study its flow field structure by simulating with attitude angle or non-design condition, determine the location of the Mach wave which reflect by composition of the shock waves at the boundary of potential core region.Give the equation of the relation between the sizes of supersonic nozzle that meet the test requirements and inlet location and the simulated attitude angle by combining with the equation of the potential core region.Design the Supersonic Free-jet Simulated Altitude Test Cell and simulate the test with different attitude angle by using CFD method. All the simulated results meet the engineering requirements. The results will provide important reference for the forecast of test effect.The purpose of this paper is to achieve the optimizing of the aerodynamic layout that of the Supersonic Free-jet Simulated Altitude Test Cell, provide basic data for its argumentation and development.