The turbine engine propulsion simulator being developed by the Air Force Aero Propulsion Laboratory is a promising wind tunnel testing tool which may be used to improve the procedure for aircraft performance prediction. This study identifies the type of applications which will afford the most successful utilization of the simulator and the model designs which will yield the best results. Three aircraft configurations have been used for this study (advanced tactical fighter, advanced bomber, and single-engine-lightweight fighter). These aircraft are representative of a wide range of engine installation types, and hence serve to identify most of the problem to be encountered in using the simulator. The first part of this report addresses how the propulsion simulator should be used with wind tunnel test models and when in the development cycle of an aircraft it should be utilized. In the second part, the feasibility of model designs incorporating the propulsion simulator is investigated. Different balance arrangements and support systems have been developed for the three aircraft configurations. The data accuracy, cost, and testing complexity for these designs have been evaluated. The last section defines a program plan for developing and evaluating wind tunnel test techniques using the propulsion simulator. (Author)


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