An Active Flow Circulation Controlled Flap Concept for General Aviation Aircraft Applications

Circulation Control Model Experimental Database for CFD Validation

“…The accurate numerical prediction of lift involves correctly modeling and/or simulating the interactions between the wall-bounded jet with both the bounding wall and the imposed freestream. 1,2,3,4 The model used in this experimental study was designed and extensively tested at the Georgia Tech Research Institute (GTRI). Under the NASA Fundamental Aeronautics Subsonic Fixed Wing Project, the model has also been tested at the NASA Langley Research Center (LaRC).…”

Flow Control over the Blunt Trailing Edge of Wind Turbine Airfoils Using Circulation Control

“…The CFD results agree very well with the experiment over almost the entire airfoil surface except the bottom trailing edge area where the local measured pressure coefficient even exceeds 2.0. This discrepancy may be due to the lack of confidence in the experimental trailing edge pressure data and the associated error magnitudes, as indicated in Jones et al [25]. The flow field with streamlines and Mach number contour is given in Figure 7, showing that the free stream is deflected significantly due to the Coanda effect at the trailing edge.…”

“…According to the test setup and test data available, the validation condition is set as AoA = 0 • , Ma = 0.10, Re = 5.33 × 10 5 , Cµ = 0.06. The pressure coefficient distribution is calculated and shown in Figure 6, and the experimental data and CFD result by Jones et al [25] using the FUN2D code are shown for comparison. The FUN2D code employed the same RANS equations in conservation-law form along with the Spalart-Allmaras turbulence model as the present solver, except that the grid is fully unstructured.…”

“…The GACC airfoil was developed in a test program intended to address some technology issues associated with CC implementation in the aeronautical application [25]. It is a supercritical airfoil model with dual slotted circulation control capability for low speed testing in the LaRC Basic Aerodynamic Research Tunnel.…”

“…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.…”