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Wind tunnel tests of the Tu-154M aircraft aerodynamic characteristics

Krzysiak Andrzej

Journal of KONES

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2019

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Vol. 26, No. 3

113--120

EN

Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s

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Necessary wind tunnel tests conditions of proper two- and three-dimensional measurements

Krzysiak A.

Journal of KONES

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2018

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Vol. 25, No. 3

315--322

EN

In this article, the conditions to be met by a two- and three dimensional wind tunnel tests in order to ensure their correctness are presented. First of all, they relate to the flow similarity between the real and wind tunnel conditions. This similarity enforces a wind tunnel calibration, a proper design and manufacturing of the tested models, a proper research, as well as processing of obtained test data including the usage of the wind tunnel corrections. In this work, the majority of these conditions were presented but in particular, the influence of the wind tunnel corrections on the tested models aerodynamic characteristics is consider. The two-dimensional airfoil studies and three-dimensional aircraft model balance investigation were performed in two low speed wind tunnels of a different sizes of theirs test section. The wind tunnel tests were performed in two Institute of Aviation low speed wind tunnels, namely in the wind tunnel T-1 (of the 1.5 m diameter test section) and in the wind tunnel T-3 (of the 5 m diameter test section), at the same undisturbed velocity, V∞ = 40 m/s. The comparison of the lift coefficient characteristic obtained in two different wind tunnels using the same two and three-dimensional models and same measurement techniques enabled to discuss the problem of necessity of the wind tunnel corrections usage.

3

Aerodynamic measurements micro air vehicle

Zyluk A., Sibilski K., Kowalski M., Wiśniowski W.

Journal of KONES

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2015

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Vol. 22, No. 4

343--353

EN

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.