Engineers at the Zhukovsky National Research Center have developed a nacelle for a promising small-sized turbofan engine with a bypass ratio of 6–7. It was designed for a turbofan engine with an air flow through the gas generator of 1.15 kg/s.

The patent specifies that the development can be used for a technology demonstrator of a promising mainline aircraft with small-sized turbofan engines, as well as for promising models of light aircraft. Among domestic engines of this class, the authors specifically mention the TRDD-200, which is under development at CIAM.

The leading edges of the air intake received a collector ratio of 12–14%, and the duct was made 0.3–0.5 engine diameters long.

The nozzle geometry was also optimized. The outer surface of the outer contour nozzle forms an angle of 20–24° with the engine axis.

According to the description of the utility model, the chosen geometry should reduce effective thrust losses and ensure separation-free flow and gas-dynamic stability of the power plant, including at high angles of attack and in crosswinds.

As a foreign benchmark, the engineers indicated the French DGEN 380 engine with a take-off thrust of about 250 kg, but its nacelle has disadvantages for the proposed turbofan engine.