By George T. K. Woo, Ari Glezer (auth.), Rudibert King (eds.)
This quantity provides an up to date and good balanced mix of theoretical and experimental cutting-edge result of lively move keep an eye on. It combines new advancements optimum open- and closed-loop keep an eye on and version relief for keep watch over. Numerical and experimental purposes are thought of from aeronautics, ground-based autos, turbo-machinery and combustors. The contributions to this ebook have been offered on the convention energetic stream keep an eye on II, held may possibly 26-28, 2010, on the Technische Universität Berlin, Germany.
Read or Download Active Flow Control II: Papers Contributed to the Conference ”Active Flow Control II 2010”, Berlin, Germany, May 26 to 28, 2010 PDF
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Extra resources for Active Flow Control II: Papers Contributed to the Conference ”Active Flow Control II 2010”, Berlin, Germany, May 26 to 28, 2010
2,3]. Enabling AFC techniques to be useful for aircraft maneuvering requires an understanding of the performance of both the AFC actuator and the flow over the flight vehicle in unsteady flow environments. David Williams . edu * Jens Pfeiffer . Rudibert King Measurement and Control Group, Technische Universität Berlin, Hardenbergstr. edu R. ): Active Flow Control II, NNFM 108, pp. 19–30. com © Springer-Verlag Berlin Heidelberg 2010 20 D. Williams et al. The challenge in using AFC to enhance aircraft maneuverability comes from the effects of unsteady aerodynamics and the substantial time delays in the flow response to actuation.
Most results in this report, refer to a flap deflection angle of 16◦ and 21◦ . 1 Unexcited Flow In preparation for the tests with active flow control, the base flow without excitation was investigated for different flap deflection angles. These studies provide information about the flap angle at which flow separation occurs on the flap. Figure 5 shows the lift (left diagram) and drag (right diagram) coefficients versus the angle of attack for different flap deflection angles. It can be seen that a magnification of the flap angle and thereby a magnification of the camber of the profile leads to an increased lift coefficient.
Oscillations in lift occur when the flow speed transient occurs, but these oscillations are damped over time. 05N. 28 D. Williams et al. Fig. 9 Step response of lift at U = 7 m/s with and without control (left). Phase averaged velocity 1/ 2 signal (top right) and control input signal, C pj , (bottom right). 25m/s. Again the controller attempts to maintain a constant lift. Figure 10 shows the power spectral density of the controlled and uncontrolled fluctuating lift. Fig. 10 Comparison of fluctuating lift signal with and without control (left), and the power spectra of both signals (right).