Experimental Determination of the Effect of Floats on Aerodynamic Characteristics of the “OSA” Aircraftin Asymmetric Flow

Michał FRANT; Michał FRANT

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Tytuł: Experimental Determination of the Effect of Floats on Aerodynamic Characteristics of the “OSA” Aircraftin Asymmetric Flow ; Experimental Determination of the Effect of Floats on Aerodynamic Characteristics of the “OSA” Aircraftin Asymmetric Flow

Abstrakt:

This study provides the results of experimental tests of the effect of floats on the aerodynamic characteristics of the “OSA” plane in an asymmetric flow. The tests were carried out in a low-speed wind tunnel owned by Institute of Aviation Technology, Faculty of Mechatronics, Armament and Aerospace (FMAA), Military University of Technology (MUT, Warsaw, Poland). The model of “OSA” was tested at dynamic pressure q = 500 Pa within the range of slip angles β = -2828. The tests were carried out for the plane model in the so-called “plain” configuration, i.e. at non-deflected control surfaces and wing mechanisation elements. The model was tested in two variants – with floats and without floats. The effect of deflection of the flaps, ailerons and rudder on the aerodynamic characteristics of the test model was also examined. The obtained values of drag coefficient, lateral force coefficient and yawing moment coefficient are presented in the form of tables and graphs. The tests showed that the floats had a significant impact on the curves of the characteristics. They result in a considerable increase of the value of the drag coefficient and in a deterioration of weathercock stability.
; This study provides the results of experimental tests of the effect of floats on the aerodynamic characteristics of the “OSA” plane in an asymmetric flow. The tests were carried out in a low-speed wind tunnel owned by Institute of Aviation Technology, Faculty of Mechatronics, Armament and Aerospace (FMAA), Military University of Technology (MUT, Warsaw, Poland). The model of “OSA” was tested at dynamic pressure q = 500 Pa within the range of slip angles β = -2828. The tests were carried out for the plane model in the so-called “plain” configuration, i.e. at non-deflected control surfaces and wing mechanisation elements. The model was tested in two variants – with floats and without floats. The effect of deflection of the flaps, ailerons and rudder on the aerodynamic characteristics of the test model was also examined. The obtained values of drag coefficient, lateral force coefficient and yawing moment coefficient are presented in the form of tables and graphs. The tests showed that the floats had a significant impact on the curves of the characteristics. They result in a considerable increase of the value of the drag coefficient and in a deterioration of weathercock stability.