By George T. K. Woo, Ari Glezer (auth.), Rudibert King (eds.)
This quantity provides an up to date and good balanced blend of theoretical and experimental state of the art result of energetic stream keep watch over. It combines new advancements optimum open- and closed-loop keep an eye on and version aid for regulate. Numerical and experimental functions are thought of from aeronautics, ground-based cars, turbo-machinery and combustors. The contributions to this ebook have been awarded on the convention lively circulate keep watch over II, held might 26-28, 2010, on the Technische Universität Berlin, Germany.
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Additional resources for Active Flow Control II: Papers Contributed to the Conference ”Active Flow Control II 2010”, Berlin, Germany, May 26 to 28, 2010
The Bode plots of these transfer functions are shown in Fig. 8. In order to obtain the controller a cost functional min N ( K ( s)) ∞ , with N = [wP S K wT T wu KS ] , T has to be minimized, wherein K(s) denotes the optimal controller . Fig. 8 Bode plots of the shaped transfer functions used in the design of the controller. Refer to text for details. 2 Controller Performance in Experiments Step input changes in the freestream speed were used to test the controller. 4N. Figure 9 shows the phase-averaged lift response over 50 cycles of the controlled case along with the uncontrolled lift.
The system consists of a frequency-doubled Nd:YLF 34 T. Grund and W. Nitsche test section sidewalls Nd:YLF laser 8 u high-speed CMOS cameras beam construction 6- component balance Fig. 2 Test section with PIV system and test model laser, two high-speed CMOS cameras and a synchronization unit, see Fig. 2. 4, centred directly above an actuator chamber. 2 Excitation System The excitation system is divided in 14 actuator segments arranged in spanwise direction. The actuator segments are placed inside the flap and are connected to a fast switching solenoid valve with compressed air supply.
In the initial attempts, all actuators were activated with the same signal. A variation of the mass flow rate as well as the frequency was carried out for a flap deflection angle of 16◦ to 21◦ . 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.