期刊名称：Eastern-European Journal of Enterprise Technologies
印刷版ISSN：1729-3774
电子版ISSN：1729-4061
出版年度：2017
卷号：5
期号：7
页码：45-52
DOI：10.15587/1729-4061.2017.109499
语种：English
出版社：PC Technology Center
摘要：We report results of experimental investigation of aerodynamic characteristics of an aircraft maneuvering model with and without a passage of airflow through the engines. During aero-tube experiment, research into the fighter aircraft models with round and rectangular shapes of nozzles was conducted. A basic method for studying aerodynamic characteristics is the weight experiment. When processing experimental data, we applied a method of corrections and calculated correction factors that depend on the shape of working part of the wind tunnel and relative dimensions of the model. The methodology for a comprehensive analysis of corrections and for determining magnitudes of the most important correction coefficients was developed, that is frontal drag and lifting force. Verification of the developed technique was carried out by comparing blowdown results of the fighter aircraft model of the MiG-29 type in the wind tunnel T-1 at Kharkiv National University of Air Forces named after Ivan Kozhedub with the results obtained from reliable semi-empirical dependences. Relative error of determining maximum aerodynamic quality of the aircraft was 3 % compared to the results of aerodynamic characteristics of the actual aircraft. The difference of the developed technique is the possibility of using interchangeable nozzles of engine imitators and the introduction of correction for the resistance of inner channels of the aircraft model’s nacelles. We demonstrated feasibility of the developed procedure for aero-tube experiment and adequacy of accounting for experimentally-determined corrections.
