Investigation of special test technique for inlet and engine matching of small-size propulsion system in high speed wind tunnels

A special test technique applied to inlet/engine matching of small-size propulsion system is developed in a high speed wind tunnel, the purpose is to predict and verify the characteristics of inlet/engine matching for the propulsion system of a small-size flying vehicle such as a cruise missile. Analysis of the aerodynamic and structural issues on the test model and support system, test plan, test methods and the related procedures, as well as the evaluation of environment pollution, test safety and model protection are represented. Tests show that the technique applied to the available intermittent wind tunnels is able to solve inlet/engine matching in the phase of ground testing, plays the roles of high altitude test beds and propulsion wind tunnels, and provides a good test environment of outer airflow simulation for small-size propulsion systems. The technique is of practical and applicable value.