Modified combined cycle engine models were tested in subsonic and transonic regions to improve the aerodynamic performance and overcome the problems which were found in the previous tests with the ejector jet prototype model. Three inlet geometries and two cowl options were tested and all models successfully reduced the inlet drag comparing to that of the prototype. In a high subsonic or transonic °ow, the current models showed the possibility of the thrust augmentation by the ejector-jet cycle. One dimensional aerodynamic estimations were also carried out and the results were compared with the data evaluated from the pitot pressure measurements. The mass °ow was in good agreement and, with a
slight adjustment of the parameter, the total pressure prediction method showed reasonable match with the experimental data.