47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2009
DOI: 10.2514/6.2009-902
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2-D Circulation Control Airfoil Benchmark Experiments Intended for CFD Code Validation

Abstract: A current NASA Research Announcement (NRA) project being conducted by Georgia Tech Research Institute (GTRI) personnel and NASA collaborators includes the development of Circulation Control (CC) blown airfoils to improve subsonic aircraft high-lift and cruise performance. The emphasis of this program is the development of CC active flow control concepts for both high-lift augmentation, drag control, and cruise efficiency. A collaboration in this project includes work by NASA research engineers, whereas CFD val… Show more

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Cited by 57 publications
(46 citation statements)
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“…For this relatively simple comparison a torque contribution is calculated for the mid-span blade element of a H-rotor VAWT using Equations (1)-(3) and the measured lift and drag characteristics, and neglects the momentum and tip losses and dynamic effects included in the DMST model. Since the variation of drag with AoA was not reported in [33], it is assumed that the CC-E0020EJ aerofoil experiences the same drag increase with AoA as the NACA0018 aerofoil, as given in Equation (7):…”
Section: Resultsmentioning
confidence: 99%
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“…For this relatively simple comparison a torque contribution is calculated for the mid-span blade element of a H-rotor VAWT using Equations (1)-(3) and the measured lift and drag characteristics, and neglects the momentum and tip losses and dynamic effects included in the DMST model. Since the variation of drag with AoA was not reported in [33], it is assumed that the CC-E0020EJ aerofoil experiences the same drag increase with AoA as the NACA0018 aerofoil, as given in Equation (7):…”
Section: Resultsmentioning
confidence: 99%
“…To eliminate low Reynolds number characteristics, such as laminar separations, the wind tunnel velocity was increased until a constant baseline drag was achieved. Using this criteria, measurements were obtained for a tunnel dynamic pressure of 718 Pa corresponding to a chord Reynolds number, R c = 0.5 M. These measurements are described in detail in [33] and have been used to evaluate the CFD procedure used in this study.…”
Section: Resultsmentioning
confidence: 99%
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“…Figure 2 shows the sketch map of the trailing edge Coanda surface design. The procedure is given as follows: (1) Copy the upper and lower surface profile lines, and translate them inward by a distance of 0.5% chord, forming lines m and n; (2) Construct a circle with the constraint that the circle is tangent to the upper and lower translated lines m and n, as well as the trailing edge line, forming three tangency points E, F and P; (3) Connect the center point O of the circle to the two tangency points E and F, respectively, and then extend the two line segments OE and OF to intersect with the upper and lower profile lines, obtaining two intersection points C Energies 2018, 11, 619 4 of 26 and D; (4) For traditional circulation control, the whole part of the circular surface EPF is treated as the Coanda surface [21,[25][26][27], as shown in Figure 2b. This traditional CC approach is denoted as full circulation control (FCC) in the present study, in order to distinguish it from the newly proposed partial circulation control (PCC) shown in Figure 2c.…”
Section: Description Of CC Airfoil Configurationsmentioning
confidence: 99%