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## Low-speed wind tunnel tests of an aircraft model at high angle of attack

### Tobiasz Dybowski

#### Abstract

The aim of this thesis is to research the aerodynamic characteristics of high maneuver aircraft at high post-stall angles of attack. The research was conducted in an a low speed wind tunnel in the laboratory of low speeds in the Institute of Aeronautics and Applied Mechanics. The tests were made on a aircraft model equipped with control surfaces enabling the changing of their position. The first part of the thesis is a theoretical introduction to the theme regards strake-wing configuration. In this part the issues of vortex flows, typical for the slender wing was introduced. The advantages and disadvantages of this configuration have been discussed along with the accompanying aerodynamic phenomenon. Further the non linearity of aerodynamics at large angles of attack and the criteria used to rate high maneuver aircraft at high angles of attack have been discussed. The second part of the thesis is the practical part in which the description of the testing facility used in the tests has been introduced. This part also contains the description of the methodology of the conducted tests, the scope of angles of attack and angles of sideslip and settings of control surfaces used. Measurements of longitudinal, directional and lateral stability and the effectiveness of aileron, elevator and rudder for a range of angles of attack from -3o to 57o. At first the research was conducted for two flap sets (30o and 25o), however due to inferior results during tests the 25o flap set was discarded. The main characteristics of the plan were resarched for a variety of sideslip angles, ranging from 2o to 20o. To show the dynamic characteristics of the aircraft a rating criteria specified for high angles of attack was used, resulting in a series of integrated Bihrle-Weissman charts. The described results show the aerodynamic properties of the designed aircraft, its stability and control effectiveness. The last part is a critical analysis of the results and conclusions stemming from them, concerning adopted solutions their configurations and effects on external factor results.
Diploma type
Engineer's / Bachelor of Science
Diploma type
Engineer's thesis
Author
Tobiasz Dybowski (FPAE) Tobiasz Dybowski,, Faculty of Power and Aeronautical Engineering (FPAE)
Title in Polish
Badania modelu samolotu w tunelu aerodynamicznym małych prędkości w zakresie dużych kątów natarcia
Supervisor
Krzysztof Kubryński (FPAE/IAAM) Krzysztof Kubryński,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Certifying unit
Faculty of Power and Aeronautical Engineering (FPAE)
Affiliation unit
The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)
Study subject / specialization
, Lotnictwo i Kosmonautyka
Language
(pl) Polish
Status
Finished
Defense Date
21-03-2016
Issue date (year)
2016
Pages
58
Internal identifier
MEL; PD-3660
Reviewers
Krzysztof Kubryński (FPAE/IAAM) Krzysztof Kubryński,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE) Konrad Gumowski (FPAE/IAAM) Konrad Gumowski,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Keywords in Polish
badania tunelowe, aerodynamika dużych kątów natarcia, stateczność i sterowność na dużych kątach natarcia
Keywords in English
wind tunnel tests, high angle of attack aerodynamics, stability and control effectiveness at high angle of attack
Abstract in Polish
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Tobiasz_Dybowski_praca_inżynierska.pdf
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Identyfikator pracy APD: 10326

Uniform Resource Identifier
urn:pw-repo:WUTe8b65862aebe4793a03776fad62d4ff2