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520 PATEL ET AL. Fig. 5 Diagram of the smart plasma slat experimental system. sensor located at the leading edge, x=c 0:05, on the suction side. This location was chosen to allow detection of incipient flow separation at the leading edge. Figure 6 shows the photograph and schematic of the airfoil model and the pressure sensor used in the experiments. As shown in Fig. 6, a slot was machined into the pressure side of the airfoil which was used to accommodate the sensor. The slot cavity was sealed by clear tape. Amplitude Peak Sense-and-Control (APSC) Method The diagram in Fig. 5 represents a block diagram for the APSC control method. To find the rule for feedback control, the characteristic of static pressure at x=c 0:05 was investigated at each angle of attack when the plasma was off and on. Figure 7 shows the fast Fourier transform (FFT) analysis of discrete sampled static pressuredataatdifferentanglesofattack.For12 degthereisno difference between the spectra with the plasma actuator off and on. However, when reaches 13 deg, which is 1 deg lower than the flow separates at the leading edge, a dominant frequency and its harmonic appears in the spectrum when the plasma actuator is on. This frequency corresponds to the unsteady forcing frequency of the plasma actuator which was 166 Hz in this case. At 14:5 deg, which is immediately after stall, a low- frequency dominates the flow when the actuator is off. This low frequency was investigated by Broeren and Bragg [25]. The results showed that the development and growth of the leading-edge position of the support sting. Its motion was controlled by the data acquisition computer through software. With this, the angular positionwasrepeatableto0:005 deg.Figure5showsthediagram of the experimental system. Feedback Control Two methods of predicting incipient flow separation at the wing leading edge were developed based on the frequency and time domain analyses of the pressure data, which were then experimentally verified via closed-loop control experiments. The APSC method is based on the detection of frequency peaks in the flowfield under the influence of an upstream unsteady actuator, and the other PASC method relies on the detection of high amplitude peaks of key pressure frequencies that are strong precursors of flow separation. In both the approaches, we track incipient separation on the upper surface of the airfoil to predict stall. The plasma actuator was operated at an a.c. amplitude of 7 kVp-p and at a modulation frequency of 166 Hz (F 1). Pressure data were sampled at 1 kHz, and lift and drag was measured on the wing using a force balance. Pressure measurements were made using a high-bandwidth pressure a) b) Static Pressure Port Pressure Sensor c) x/ c = 5% NACA 0015 a) Photograph of 2-D NACA 0015 airfoil model with a fast- Fig. 6 response pressure sensor; b) close view of the pressure sensor; c) schematic of NACA 0015 airfoil with a pressure sensor and location of the pressure port. Power spectrum of discrete sampled static pressure at 8, 13, Fig. 7 14.5, and 22 deg when plasma actuator is turned off and on.PDF Image | Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat
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