Autor: Wiśniowski, A. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Influence of the ballistic protection on aerodynamic helicopter characteristics
Autorzy:: Wisniewski, A.
Wisniowski, W.
Powiązania:: https://bibliotekanauki.pl/articles/244913.pdf
Data publikacji:: 2016
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: passive ballistic protection
aerodynamic coefficient
stabiliser
helicopter fuselage
Opis:: This paper contains results of experimental tests of the influence of passive ballistic protection on aerodynamic coefficients of the model fuselage of the Sokol helicopter. The research was carried out in the Institute of Aviation low speed wind tunnel T3 of 5 m diameter on the helicopter test stand. Measurements of aerodynamic coefficients acting on the fuselage with and without passive ballistic protection were taken using six–component internal strain gauge balance placed inside the model of the fuselage for the angles of attack α = –90-90° with step 10° and for sideslip angles β = –10°, 0°, 10°. Several aerodynamics coefficients: drag (Cx), force (Cy), lift (Cz) and moment: bank (Cmx), pitch (Cmy) and yaw (Cmz) were analysed. The results of the wind tunnel tests were presented in figures as non-dimensional mean values of the above aerodynamic coefficients. Different measurements of aerodynamic characteristics were made like: the influence of Reynolds number on the Cx of the helicopter fuselage with and without protection and the comparison of aerodynamic characteristics of the helicopter fuselage Cx, Cy, Cz, Cmx, Cmy, Cmz as the function of α, without stabiliser, with and without protection. Moreover, a comparison Cx, Cy, Cz, Cmx, Cmy, Cmz as the function of α, with a stabiliser, with and without protection was made and a comparison of the influence of a stabiliser and protection on the above aerodynamic characteristics for the range of useful angles of attack were analysed. A comparison of the influence of a stabiliser and protection on aerodynamic characteristics of the helicopter fuselage Cx, Cy, Cz, Cmx, Cmy, Cmz for the range of α angles of attack was also described.
Źródło:: Journal of KONES; 2016, 23, 4; 549-554
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Aerodynamic measurements micro air vehicle
Autorzy:: Zyluk, A.
Sibilski, K.
Kowalski, M.
Wiśniowski, W.
Powiązania:: https://bibliotekanauki.pl/articles/243837.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: construction of micro air vehicles
aerodynamic measurements
Opis:: In present times, constructions of micro air vehicles arouse more and more interest researchers and manufacturers. Air turbulence is perceived as a major problem for Micro Air Vehicles (MAV) in outdoor applications. According to the literature, short duration vertical gusts may have velocity comparable to MAV airspeed, so brief periods of flight at very large angles of attack have to be considered. In these circumstances, it seems reasonable to apply the design with as high stall angle of attack as possible. In particular, the flow has to be attached to control surfaces to perform effective control in order to damp air turbulence effect. Therefore, an aircraft configuration was developed with cranked delta wing and propeller located inside the wing contour. To prove the value of the concept, wind tunnel experiment was undertaken. The prototype demonstrated ability to fly controllably at extremely high angles of attack. Moreover we present few disadvantages of these construction for example it was very sensitive to the motor settings, since every rpm change required immediate airplane trimming to maintain straight path of flight. This drawback can be eliminated by application of counter-rotating propeller. The status of the program is presented in the paper, including the most recent results, as well as currently undertaken experiments and plans for the nearest future.
Źródło:: Journal of KONES; 2015, 22, 4; 343-353
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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