Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow
This paper presents the results of experimental determination of the impact of floats on the aerodynamic characteristics of an OSA model in symmetric flow. The studies have been performed in the low-speed wind tunnel at the Military University of Technology (MUT, Warsaw, Poland). The aircraft model...
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| Format: | Article |
| Language: | English |
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Military University of Technology, Warsaw
2021-03-01
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| Series: | Problemy Mechatroniki |
| Subjects: | |
| Online Access: | http://promechjournal.pl/gicid/01.3001.0014.7850 |
| _version_ | 1826954295292985344 |
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| author | Michał FRANT Stanisław WRZESIEŃ Maciej MAJCHER |
| author_facet | Michał FRANT Stanisław WRZESIEŃ Maciej MAJCHER |
| author_sort | Michał FRANT |
| collection | DOAJ |
| description | This paper presents the results of experimental determination of the impact of floats on the aerodynamic characteristics of an OSA model in symmetric flow. The studies have been performed in the low-speed wind tunnel at the Military University of Technology (MUT, Warsaw, Poland). The aircraft model was examined at the dynamic pressure q = 500 Pa in the following angle of attack range alfa= -28 to+28 deg. The investigations have been performed for an aircraft model under plain configuration with floats and without floats. The influence of elevator and flap inclination on the aerodynamic characteristics of the model has also been analysed. The obtained values of aerodynamic drag coefficient, lift coefficient, pitching moment coefficient and lift-to-drag ratio have been presented in the form of tables and graphs.
The studies performed demonstrated that the use of floats causes the increase of aerodynamic drag coefficient CD, maximum lift coefficient CLmax as well as critical angle of attack alfa cr. The decrease of lift-to-drag ratio has also been observed. Its value in the case of the model with floats was up to 20% lower than in the model without floats. The studies also showed that the model equipped with floats had a lower longitudinal static stability margin than the model without floats. |
| first_indexed | 2024-04-11T08:52:32Z |
| format | Article |
| id | doaj.art-04934017d5824dfdaebe9613a85ecc9a |
| institution | Directory Open Access Journal |
| issn | 2081-5891 |
| language | English |
| last_indexed | 2025-02-17T23:34:53Z |
| publishDate | 2021-03-01 |
| publisher | Military University of Technology, Warsaw |
| record_format | Article |
| series | Problemy Mechatroniki |
| spelling | doaj.art-04934017d5824dfdaebe9613a85ecc9a2024-12-02T03:45:50ZengMilitary University of Technology, WarsawProblemy Mechatroniki2081-58912021-03-01121415810.5604/01.3001.0014.785001.3001.0014.7850Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric FlowMichał FRANT0Stanisław WRZESIEŃ1Maciej MAJCHER2Military University of Technology, Faculty of Mechatronics, Armament and Aerospace, Institute of Aviation Technology, Warsaw, PolandMilitary University of Technology, Faculty of Mechatronics, Armament and Aerospace, Institute of Aviation Technology, Warsaw, PolandMilitary University of Technology, Faculty of Mechatronics, Armament and Aerospace, Institute of Aviation Technology, Warsaw, PolandThis paper presents the results of experimental determination of the impact of floats on the aerodynamic characteristics of an OSA model in symmetric flow. The studies have been performed in the low-speed wind tunnel at the Military University of Technology (MUT, Warsaw, Poland). The aircraft model was examined at the dynamic pressure q = 500 Pa in the following angle of attack range alfa= -28 to+28 deg. The investigations have been performed for an aircraft model under plain configuration with floats and without floats. The influence of elevator and flap inclination on the aerodynamic characteristics of the model has also been analysed. The obtained values of aerodynamic drag coefficient, lift coefficient, pitching moment coefficient and lift-to-drag ratio have been presented in the form of tables and graphs. The studies performed demonstrated that the use of floats causes the increase of aerodynamic drag coefficient CD, maximum lift coefficient CLmax as well as critical angle of attack alfa cr. The decrease of lift-to-drag ratio has also been observed. Its value in the case of the model with floats was up to 20% lower than in the model without floats. The studies also showed that the model equipped with floats had a lower longitudinal static stability margin than the model without floats.http://promechjournal.pl/gicid/01.3001.0014.7850mechanical engineeringaerodynamicswind tunnelflow around aircraft model |
| spellingShingle | Michał FRANT Stanisław WRZESIEŃ Maciej MAJCHER Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow Problemy Mechatroniki mechanical engineering aerodynamics wind tunnel flow around aircraft model |
| title | Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow |
| title_full | Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow |
| title_fullStr | Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow |
| title_full_unstemmed | Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow |
| title_short | Experimental Determination of the Impact of Floats on the Aerodynamic Characteristics of an OSA Model in Symmetric Flow |
| title_sort | experimental determination of the impact of floats on the aerodynamic characteristics of an osa model in symmetric flow |
| topic | mechanical engineering aerodynamics wind tunnel flow around aircraft model |
| url | http://promechjournal.pl/gicid/01.3001.0014.7850 |
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