The method of advanced bypass turbojet engine core research tests with simulation of target inlet thermogasdynamic parameters at the engine OEM site is considered. It is stated that research testing is traditionally associated with the use of multifunctional test facilities capable of simulat-ing operating conditions as close as possible to operational ones for a wide range of test objects of different thrust (power) and application. Such test facilities require significant investment and operating costs, which in general determines their limited number in the world. It is shown that the steady growth of the share of research tests at the initial design stages requires organization of tests with minimal financial and material costs directly at the engine OEM site, where testing the advanced bypass turbojet engine core plays a special part. Determination of the method for simulating thermogasdynamic parameters is associated with solution of rather contradictory problems, where, on the one hand, it is required to ensure reliable reproduction of the actual operating conditions of the core for all configurations of the bypass turbojet engine under development, and on the other hand, to ensure lower manpower and cost of testing. One of the effective solutions is the use of specialized test facilities, a distinctive feature of which is determination of the simplest and most economical means of obtaining the working fluid with the required thermogasdynamic parameters for a pre-determined range of test objects of different thrust (power) and application. The technical implementation of the dedicated test facility for testing the advanced bypass turbojet engine core at UEC-Aviadvigatel JSC (Perm) is considered.