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    FLOW AROUND A SQUARE PRISM AND A CIRCULAR CYLINDER IN TANDEM ARRANGEMENT
    (TECH UNIV LIBEREC, FAC MECHANICAL ENG, 2010) Akansu, Yahya Erkan; Yavuz, Tahir; Sarioglu, Mustafa; Vit, T; Dancova, P
    Aerodynamic characteristics of flow around two bluff bodies of square and circular section in a tandem arrangement have been investigated experimentally at a Reynolds number of 2.2 x 10(4). Experiments were carried out in a wind tunnel for the various values of distance between the bodies in the range of 1 <= L/D <= 10. The upstream square prism side length and downstream circular cylinder diameter were equal to 25 mm. By using pressure transducer and hot-wire anemometer, mean pressure distributions and vortex-shedding from the square prism and circular cylinder were examined. Drag and lift coefficients were obtained from the integration of the pressure distributions. The Strouhal numbers of the test models were determined from the frequency analysis of the velocity fluctuations. A single smoke-wire was set in front of the bodies and the flow structure at the mid-span of test section was visualized at Re=7.0x10(3). Depending on the distance between the bodies, the positions of flow attachments, separations, reattachments and the structures of the vortex formation region have been clearly obtained from the flow visualization. According to the results, there are three basic flow structures in the case of the two tandem body arrangement depending on the distance between the bodies. These are "pattern I: single body behavior", "pattern II: shear layer reattachment" and "pattern III: vortex shedding between two bodies".
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    Flow field and heat transfer characteristics in an oblique slot jet impinging on a flat plate
    (PERGAMON-ELSEVIER SCIENCE LTD, 2008) Akansu, Yahya Erkan; Sarioglu, Mustafa; Kuvvet, Kemal; Yavuz, Tahir
    An experimental study was performed to determine the effects of inclination of an impinging two dimensional slot jet on the heat transfer from a flat plate. Local Nusselt numbers and surface pressure distributions were determined depending on inclination angle, jet-to-plate spacing and Reynolds number. The results showed that the location of maximum heat transfer was mainly due to the angle of inclination. As the inclination angle increases, the location of the maximum heat transfer shifts towards the uphill side of the plate and the value of the maximum Nusselt number gradually increases at lower jet-to-plate spacings. (C) 2008 Elsevier Ltd. All rights reserved.
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    Influence of Leading-Edge Tubercle with Amplitude Modulation on NACA 0015 Airfoil
    (Amer Inst Aeronautics Astronautics, 2021) Seyhan, Mehmet; Sarioglu, Mustafa; Akansu, Yahya E.
    Flow around a NACA0015 airfoil with leading-edge tubercles was investigated using force measurements and flow visualization at 0 deg <= alpha <= 30 deg. The experiments were carried out at a low Reynolds number of Re = 6.3 x 10(4), where the transition to turbulent flow still occurred on the suction side of the airfoil. The leading-edge patterns of the models were produced by using only either one wave function or one superposition of two wave functions. Two tubercle models with uniform distribution and nine more realistic biomimicked airfoil models with amplitude modulation in tubercle geometry were tested in experiments. Force measurements showed that when compared to the baseline model, models with tubercles did not experience a sudden loss of lift and have higher lift coefficients in the poststall regime, irrespective of the model. It was found that the W15 model performs best in terms of maximum lift coefficient, stall angle, aerodynamic performance (C-L/C-D) in the poststall regime; as well as in terms of the minimum fluctuating lift coefficient C-L' in both pre- and poststall regimes. Enhancement of aerodynamic performance is due to the presence of stall cell formation with the counter-rotating vortex pairs and three-dimensional spanwise flow pattern initiated by leading-edge tubercles at the poststall regime.