Methodological Aspects of Determining Thrust of Irrotational Air-Breathing Jet Engines in Bench and Flight Tests

This article examines methodological aspects of the indirect calculation of thrust characteristics of irrotational air-breathing jet engines using telemetry data that can be obtained during high-speed aircraft flight tests. Specific features of determining thrust characteristics during bench and flight tests are described. Mathematical models are developed for data analysis and calculation of the thrust and the specific impulse of an irrotational air-breathing jet engine by internal parameters, as well as its effective thrust in integration with a high-speed aircraft. The proposed approaches are tested, and the developed mathematical models are validated according to the results of experimental bench tests of the thrust characteristics of irrotational air-breathing jet engines in integration with a model fuselage of a high-speed aircraft. Satisfactory convergence of the results of indirect and direct (experimental) force measurements is shown. The data obtained can be used for further development of the method and analysis of bench and flight tests of aircraft with irrotational air-breathing jet engines.

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