Experimental research into aerodynamic characteristics of a nacelle with the enabled system of engine thrust neutralization

Authors

DOI:

https://doi.org/10.15587/1729-4061.2018.147986

Keywords:

thrust reverse, thrust neutralization, fan, nacelle, two­circuit engine, wind tunnel, run distance

Abstract

We have conducted an experimental study into aerodynamic characteristics of the structural scheme “wing ‒ two­circuit engine nacelle”. The data were acquired in the course of work of a promising system for the neutralization of a two­circuit engine’s thrust of a large by­pass ratio at aircraft landing. The relevance of the conducted study relates to the improvement of operational performance of a passenger aircraft. Based on the analysis of functions and principal schemes of reversible devices at cargo and passenger airplanes, we have proposed a promising method to neutralize the thrust of a two­circuit engine with a high by­pass ratio. Physical essence of the method for neutralization of the engine’s thrust is to substantially restrict an airflow into the engine by a technique to rotate working blades of the fan at the time of landing. We have devised a specialized procedure for conducting a weighting and drainage experiment with a model of the nacelle of a turbojet two­circuit engine in a wind tunnel. The obtained experimental data make it possible to evaluate the limits of the investigated method for neutralizing the thrust in order to shorten the length of aircraft run. By conducting a drainage experiment and applying a tuft flow visualization technique, we identified the detachment of a flow at the outer surface of the nacelle’s model with a completely closed entrance. The presence of the flow detachment predetermined an increase in the frontal drag of the nacelle model by approximately 2.5 times, revealed by the weight experiment. In the course of the weight experiment it was established that the existence of a screening surface (while the engine’s nacelle approaches a runway) increases frontal drag of the nacelle model by approximately 14 %. The drainage experiment found that such an increase in the frontal drag was due to a significant redistribution of pressure at the surface of the nacelle model. The study has shown that the idea of closing the entrance to the engine that has a large by­pass ratio at the time of aircraft landing is one of the promising methods for shortening the run length of the aircraft

Author Biographies

Vasiliy Loginov, National Aerospace University Kharkiv Aviation Institute Chkalov str., 17, Kharkiv, Ukraine, 61000

Doctor of Technical Sciences, Senior Researcher

Department of Aircraft Engine Design

Yevhen Ukrainets, Ivan Kozhedub Kharkiv National University of Air Force Sumska str., 77/79, Kharkiv, Ukraine, 61023

Doctor of Technical Sciences, Professor

Department of the Design and Strength of Aircraft and Engines

Igor Kravchenko, State Enterprise "Ivchenko-Progress" Ivanova str., 2, Zaporizhia, Ukraine, 69068

Doctor of Technical Sciences, Assistant Professor, Director of the enterprise

Alexandr Yelanskiy, State Enterprise "Ivchenko-Progress" Ivanova str., 2, Zaporizhia, Ukraine, 69068

PhD

Department of Advanced Development and Gas Dynamic Calculations

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Published

2018-11-22

How to Cite

Loginov, V., Ukrainets, Y., Kravchenko, I., & Yelanskiy, A. (2018). Experimental research into aerodynamic characteristics of a nacelle with the enabled system of engine thrust neutralization. Eastern-European Journal of Enterprise Technologies, 6(8 (96), 65–73. https://doi.org/10.15587/1729-4061.2018.147986

Issue

Vol. 6 No. 8 (96) (2018): Energy-saving technologies and equipment

Section

Energy-saving technologies and equipment

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Copyright (c) 2018 Vasiliy Loginov, Yevhen Ukrainets, Igor Kravchenko, Alexandr Yelanskiy

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